GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.69 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe629-il-1000000-n5.txt Download as CSV file: xf-goe629-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 629 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9164 0.09116 0.08806 -0.0597 1.0000 0.0149
-17.250 -0.9938 0.07632 0.07300 -0.0683 1.0000 0.0142
-17.000 -1.1566 0.04869 0.04487 -0.0853 1.0000 0.0129
-16.750 -1.2018 0.03783 0.03373 -0.0939 1.0000 0.0128
-16.500 -1.2203 0.03288 0.02860 -0.0968 1.0000 0.0129
-16.250 -1.2316 0.02996 0.02556 -0.0968 1.0000 0.0131
-16.000 -1.2394 0.02799 0.02350 -0.0951 1.0000 0.0132
-15.750 -1.2460 0.02657 0.02199 -0.0923 1.0000 0.0134
-15.500 -1.2535 0.02551 0.02085 -0.0884 1.0000 0.0137
-15.250 -1.2565 0.02464 0.01991 -0.0846 0.9996 0.0139
-15.000 -1.2397 0.02344 0.01863 -0.0847 0.9973 0.0145
-14.750 -1.2198 0.02238 0.01751 -0.0849 0.9944 0.0152
-14.500 -1.1995 0.02141 0.01646 -0.0849 0.9916 0.0161
-14.250 -1.1781 0.02056 0.01555 -0.0848 0.9887 0.0169
-14.000 -1.1557 0.01965 0.01459 -0.0850 0.9862 0.0182
-13.500 -1.1057 0.01798 0.01284 -0.0860 0.9828 0.0222
-13.250 -1.0855 0.01721 0.01205 -0.0854 0.9792 0.0254
-13.000 -1.0618 0.01652 0.01134 -0.0853 0.9762 0.0286
-12.750 -1.0355 0.01590 0.01070 -0.0856 0.9741 0.0320
-12.500 -1.0074 0.01531 0.01010 -0.0863 0.9724 0.0354
-12.250 -0.9772 0.01477 0.00954 -0.0873 0.9711 0.0385
-12.000 -0.9483 0.01434 0.00909 -0.0879 0.9691 0.0413
-11.750 -0.9240 0.01392 0.00866 -0.0875 0.9648 0.0440
-11.500 -0.8953 0.01354 0.00827 -0.0880 0.9618 0.0465
-11.250 -0.8648 0.01319 0.00789 -0.0888 0.9594 0.0486
-11.000 -0.8336 0.01282 0.00751 -0.0898 0.9571 0.0510
-10.500 -0.7801 0.01229 0.00692 -0.0896 0.9478 0.0545
-10.250 -0.7503 0.01196 0.00659 -0.0902 0.9432 0.0569
-10.000 -0.7236 0.01172 0.00633 -0.0900 0.9373 0.0594
-9.750 -0.6967 0.01150 0.00607 -0.0899 0.9304 0.0611
-9.500 -0.6680 0.01130 0.00582 -0.0901 0.9247 0.0625
-9.250 -0.6437 0.01106 0.00556 -0.0894 0.9169 0.0644
-9.000 -0.6168 0.01084 0.00532 -0.0892 0.9096 0.0667
-8.750 -0.5914 0.01067 0.00511 -0.0887 0.9015 0.0686
-8.500 -0.5648 0.01052 0.00490 -0.0883 0.8929 0.0699
-8.250 -0.5392 0.01036 0.00469 -0.0878 0.8848 0.0706
-8.000 -0.5136 0.01018 0.00446 -0.0873 0.8773 0.0717
-7.750 -0.4882 0.00997 0.00423 -0.0867 0.8708 0.0735
-7.500 -0.4627 0.00979 0.00403 -0.0862 0.8637 0.0752
-7.250 -0.4368 0.00964 0.00383 -0.0857 0.8571 0.0766
-7.000 -0.4110 0.00949 0.00366 -0.0852 0.8494 0.0780
-6.750 -0.3850 0.00938 0.00348 -0.0847 0.8418 0.0793
-6.500 -0.3588 0.00926 0.00333 -0.0843 0.8341 0.0803
-6.250 -0.3329 0.00914 0.00317 -0.0837 0.8264 0.0817
-6.000 -0.3070 0.00899 0.00300 -0.0832 0.8193 0.0839
-5.750 -0.2812 0.00886 0.00284 -0.0827 0.8115 0.0861
-5.500 -0.2551 0.00874 0.00270 -0.0822 0.8042 0.0883
-5.250 -0.2290 0.00864 0.00257 -0.0818 0.7959 0.0905
-5.000 -0.2030 0.00854 0.00245 -0.0812 0.7876 0.0932
-4.750 -0.1772 0.00842 0.00233 -0.0807 0.7781 0.0974
-4.500 -0.1512 0.00833 0.00222 -0.0802 0.7693 0.1020
-4.250 -0.1255 0.00823 0.00213 -0.0796 0.7599 0.1090
-4.000 -0.0992 0.00815 0.00204 -0.0791 0.7509 0.1150
-3.750 -0.0737 0.00808 0.00196 -0.0785 0.7400 0.1215
-3.500 -0.0478 0.00804 0.00189 -0.0780 0.7267 0.1270
-3.250 -0.0224 0.00802 0.00183 -0.0773 0.7113 0.1311
-3.000 0.0026 0.00799 0.00177 -0.0766 0.6943 0.1366
-2.750 0.0279 0.00800 0.00172 -0.0759 0.6779 0.1411
-2.500 0.0534 0.00801 0.00168 -0.0752 0.6619 0.1437
-2.250 0.0785 0.00801 0.00163 -0.0745 0.6452 0.1477
-2.000 0.1033 0.00803 0.00160 -0.0737 0.6268 0.1517
-1.750 0.1283 0.00806 0.00157 -0.0730 0.6090 0.1553
-1.500 0.1535 0.00811 0.00155 -0.0723 0.5919 0.1582
-1.250 0.1790 0.00814 0.00153 -0.0717 0.5775 0.1611
-1.000 0.2044 0.00815 0.00152 -0.0710 0.5648 0.1668
-0.750 0.2301 0.00816 0.00151 -0.0705 0.5546 0.1717
-0.500 0.2564 0.00816 0.00151 -0.0700 0.5460 0.1763
-0.250 0.2821 0.00814 0.00150 -0.0694 0.5380 0.1857
0.000 0.3083 0.00813 0.00151 -0.0690 0.5311 0.1944
0.250 0.3341 0.00811 0.00152 -0.0684 0.5234 0.2071
0.500 0.3596 0.00810 0.00153 -0.0679 0.5161 0.2242
0.750 0.3851 0.00803 0.00155 -0.0673 0.5088 0.2521
1.000 0.4102 0.00800 0.00158 -0.0666 0.5022 0.2798
1.250 0.4360 0.00795 0.00161 -0.0661 0.4965 0.3039
1.500 0.4615 0.00792 0.00165 -0.0655 0.4899 0.3287
1.750 0.4862 0.00789 0.00170 -0.0648 0.4826 0.3595
2.000 0.5110 0.00787 0.00174 -0.0641 0.4712 0.3909
2.250 0.5347 0.00788 0.00180 -0.0632 0.4560 0.4265
2.500 0.5581 0.00788 0.00187 -0.0622 0.4405 0.4672
2.750 0.5807 0.00790 0.00194 -0.0611 0.4218 0.5104
3.000 0.6013 0.00797 0.00204 -0.0596 0.3944 0.5593
3.250 0.6196 0.00812 0.00218 -0.0577 0.3594 0.6149
3.500 0.6374 0.00816 0.00234 -0.0556 0.3365 0.6877
3.750 0.6546 0.00814 0.00248 -0.0533 0.3196 0.7679
4.000 0.6700 0.00809 0.00266 -0.0505 0.3024 0.8619
4.250 0.7246 0.00830 0.00298 -0.0564 0.2852 0.9490
4.500 0.7768 0.00857 0.00321 -0.0617 0.2717 0.9665
4.750 0.8142 0.00881 0.00339 -0.0639 0.2578 0.9746
5.000 0.8444 0.00911 0.00359 -0.0645 0.2396 0.9830
5.250 0.8777 0.00951 0.00385 -0.0659 0.2117 0.9908
5.750 0.9465 0.01044 0.00447 -0.0694 0.1590 1.0000
6.000 0.9620 0.01073 0.00469 -0.0669 0.1459 1.0000
6.250 0.9781 0.01100 0.00491 -0.0645 0.1341 1.0000
6.500 0.9930 0.01133 0.00516 -0.0620 0.1200 1.0000
6.750 1.0078 0.01166 0.00543 -0.0594 0.1066 1.0000
7.000 1.0232 0.01198 0.00568 -0.0570 0.0963 1.0000
7.250 1.0373 0.01225 0.00592 -0.0543 0.0890 1.0000
7.500 1.0497 0.01257 0.00619 -0.0513 0.0810 1.0000
7.750 1.0652 0.01282 0.00643 -0.0488 0.0766 1.0000
8.000 1.0793 0.01316 0.00673 -0.0463 0.0692 1.0000
8.250 1.0938 0.01353 0.00706 -0.0438 0.0611 1.0000
8.750 1.1182 0.01458 0.00795 -0.0384 0.0373 1.0000
9.000 1.1338 0.01499 0.00835 -0.0364 0.0342 1.0000
9.250 1.1500 0.01539 0.00876 -0.0345 0.0327 1.0000
9.500 1.1662 0.01581 0.00919 -0.0327 0.0315 1.0000
9.750 1.1814 0.01630 0.00968 -0.0307 0.0299 1.0000
10.000 1.1983 0.01671 0.01012 -0.0291 0.0294 1.0000
10.250 1.2146 0.01717 0.01060 -0.0274 0.0288 1.0000
10.500 1.2306 0.01766 0.01112 -0.0258 0.0283 1.0000
10.750 1.2460 0.01819 0.01168 -0.0242 0.0278 1.0000
11.000 1.2610 0.01877 0.01228 -0.0225 0.0273 1.0000
11.250 1.2754 0.01940 0.01293 -0.0209 0.0268 1.0000
11.500 1.2890 0.02009 0.01365 -0.0192 0.0262 1.0000
11.750 1.3016 0.02086 0.01445 -0.0175 0.0256 1.0000
12.000 1.3151 0.02161 0.01524 -0.0159 0.0253 1.0000
12.250 1.3293 0.02233 0.01600 -0.0146 0.0250 1.0000
12.500 1.3424 0.02314 0.01685 -0.0131 0.0247 1.0000
12.750 1.3555 0.02397 0.01772 -0.0118 0.0243 1.0000
13.000 1.3680 0.02487 0.01867 -0.0105 0.0240 1.0000
13.250 1.3800 0.02582 0.01967 -0.0092 0.0236 1.0000
13.500 1.3906 0.02691 0.02080 -0.0080 0.0233 1.0000
13.750 1.4011 0.02804 0.02197 -0.0068 0.0228 1.0000
14.000 1.4103 0.02930 0.02327 -0.0056 0.0225 1.0000
14.250 1.4186 0.03066 0.02469 -0.0044 0.0223 1.0000
14.500 1.4250 0.03223 0.02631 -0.0033 0.0218 1.0000
14.750 1.4295 0.03403 0.02817 -0.0023 0.0214 1.0000
15.000 1.4380 0.03553 0.02972 -0.0015 0.0213 1.0000
15.250 1.4463 0.03709 0.03134 -0.0008 0.0210 1.0000
15.500 1.4529 0.03885 0.03318 -0.0002 0.0208 1.0000
15.750 1.4603 0.04059 0.03497 0.0003 0.0205 1.0000
16.000 1.4652 0.04262 0.03708 0.0007 0.0203 1.0000
16.250 1.4713 0.04456 0.03908 0.0010 0.0199 1.0000
16.500 1.4754 0.04680 0.04138 0.0013 0.0196 1.0000
16.750 1.4779 0.04925 0.04390 0.0014 0.0194 1.0000
17.000 1.4801 0.05179 0.04651 0.0014 0.0192 1.0000
17.250 1.4815 0.05445 0.04923 0.0013 0.0189 1.0000
17.500 1.4812 0.05739 0.05225 0.0010 0.0187 1.0000
17.750 1.4799 0.06051 0.05543 0.0007 0.0183 1.0000
18.000 1.4751 0.06412 0.05911 0.0001 0.0180 1.0000
18.250 1.4694 0.06788 0.06296 -0.0006 0.0180 1.0000
18.500 1.4697 0.07091 0.06608 -0.0011 0.0177 1.0000
18.750 1.4647 0.07471 0.06997 -0.0020 0.0176 1.0000
19.000 1.4636 0.07801 0.07334 -0.0027 0.0173 1.0000
19.250 1.4582 0.08191 0.07733 -0.0037 0.0171 1.0000
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