GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.24 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe509-il-1000000.txt Download as CSV file: xf-goe509-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 509 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6110 0.03431 0.03203 -0.0905 0.9775 0.0122
-10.500 -0.6140 0.02485 0.02176 -0.0933 0.9738 0.0123
-10.250 -0.5950 0.02144 0.01795 -0.0943 0.9723 0.0127
-10.000 -0.5600 0.02024 0.01664 -0.0966 0.9715 0.0132
-9.750 -0.5456 0.01957 0.01588 -0.0941 0.9667 0.0134
-9.500 -0.5178 0.01869 0.01489 -0.0946 0.9643 0.0138
-9.250 -0.4900 0.01758 0.01361 -0.0950 0.9621 0.0141
-9.000 -0.4586 0.01673 0.01262 -0.0961 0.9602 0.0146
-8.750 -0.4270 0.01590 0.01163 -0.0971 0.9579 0.0150
-8.500 -0.4111 0.01540 0.01103 -0.0945 0.9517 0.0152
-8.250 -0.3877 0.01430 0.00980 -0.0939 0.9469 0.0161
-8.000 -0.3602 0.01379 0.00922 -0.0937 0.9429 0.0166
-7.750 -0.3404 0.01350 0.00890 -0.0919 0.9356 0.0172
-7.500 -0.3134 0.01313 0.00844 -0.0916 0.9300 0.0179
-7.250 -0.2930 0.01277 0.00801 -0.0898 0.9198 0.0185
-7.000 -0.2720 0.01209 0.00721 -0.0883 0.9058 0.0191
-6.750 -0.2458 0.01160 0.00664 -0.0878 0.8792 0.0200
-6.500 -0.2183 0.01142 0.00625 -0.0874 0.8419 0.0208
-6.250 -0.1947 0.01128 0.00595 -0.0864 0.8194 0.0216
-6.000 -0.1704 0.01116 0.00569 -0.0854 0.8058 0.0224
-5.750 -0.1476 0.01074 0.00515 -0.0843 0.7945 0.0236
-5.500 -0.1227 0.01059 0.00499 -0.0836 0.7849 0.0247
-5.250 -0.0978 0.01050 0.00482 -0.0828 0.7753 0.0257
-5.000 -0.0725 0.01037 0.00463 -0.0821 0.7660 0.0269
-4.750 -0.0479 0.01013 0.00431 -0.0812 0.7576 0.0278
-4.500 -0.0240 0.00980 0.00395 -0.0803 0.7488 0.0295
-4.250 0.0014 0.00972 0.00383 -0.0797 0.7396 0.0308
-4.000 0.0262 0.00959 0.00364 -0.0789 0.7298 0.0321
-3.750 0.0520 0.00951 0.00352 -0.0782 0.7210 0.0331
-3.250 0.1005 0.00901 0.00293 -0.0764 0.7028 0.0367
-3.000 0.1254 0.00892 0.00281 -0.0757 0.6934 0.0385
-2.750 0.1504 0.00885 0.00267 -0.0749 0.6823 0.0396
-2.500 0.1742 0.00863 0.00240 -0.0739 0.6702 0.0421
-2.250 0.1981 0.00854 0.00227 -0.0729 0.6553 0.0443
-2.000 0.2219 0.00849 0.00216 -0.0719 0.6384 0.0464
-1.750 0.2450 0.00853 0.00209 -0.0707 0.6169 0.0483
-1.500 0.2669 0.00844 0.00192 -0.0693 0.5904 0.0529
-1.250 0.2877 0.00854 0.00186 -0.0677 0.5515 0.0570
-1.000 0.3063 0.00872 0.00182 -0.0657 0.4954 0.0632
-0.750 0.3272 0.00886 0.00183 -0.0642 0.4640 0.0714
-0.500 0.3494 0.00884 0.00181 -0.0630 0.4495 0.0900
-0.250 0.3709 0.00874 0.00179 -0.0616 0.4398 0.1338
0.000 0.3910 0.00854 0.00184 -0.0600 0.4323 0.2310
0.250 0.4145 0.00858 0.00189 -0.0591 0.4248 0.2599
0.500 0.4389 0.00861 0.00193 -0.0583 0.4189 0.2778
0.750 0.4630 0.00868 0.00198 -0.0574 0.4137 0.2901
1.000 0.4871 0.00872 0.00203 -0.0566 0.4095 0.3025
1.250 0.5119 0.00872 0.00206 -0.0559 0.4061 0.3153
1.500 0.5363 0.00875 0.00210 -0.0551 0.4024 0.3279
1.750 0.5600 0.00880 0.00215 -0.0542 0.3979 0.3408
2.000 0.5833 0.00885 0.00221 -0.0532 0.3935 0.3545
2.250 0.6071 0.00880 0.00226 -0.0523 0.3905 0.3856
2.500 0.6123 0.00798 0.00227 -0.0476 0.3876 0.7104
2.750 0.7478 0.00807 0.00296 -0.0719 0.3763 0.9742
3.000 0.7867 0.00826 0.00314 -0.0743 0.3726 0.9813
3.250 0.8250 0.00843 0.00328 -0.0766 0.3684 0.9852
3.500 0.8674 0.00862 0.00340 -0.0800 0.3608 0.9879
3.750 0.9062 0.00871 0.00350 -0.0825 0.3561 0.9906
4.000 0.9420 0.00887 0.00362 -0.0844 0.3499 0.9935
4.250 0.9819 0.00896 0.00368 -0.0872 0.3430 0.9953
4.500 1.0200 0.00905 0.00373 -0.0897 0.3340 0.9972
4.750 1.0560 0.00914 0.00380 -0.0917 0.3257 0.9989
5.000 1.0880 0.00928 0.00387 -0.0928 0.3116 1.0000
5.250 1.1078 0.00946 0.00400 -0.0913 0.2976 1.0000
5.500 1.1260 0.00973 0.00416 -0.0895 0.2764 1.0000
5.750 1.1415 0.01013 0.00441 -0.0872 0.2481 1.0000
6.000 1.1557 0.01060 0.00471 -0.0846 0.2197 1.0000
6.500 1.1871 0.01138 0.00530 -0.0801 0.1865 1.0000
6.750 1.2052 0.01163 0.00553 -0.0783 0.1795 1.0000
7.000 1.2222 0.01192 0.00578 -0.0763 0.1725 1.0000
7.250 1.2399 0.01217 0.00603 -0.0744 0.1667 1.0000
7.500 1.2562 0.01246 0.00629 -0.0723 0.1597 1.0000
7.750 1.2728 0.01273 0.00655 -0.0702 0.1541 1.0000
8.000 1.2888 0.01299 0.00680 -0.0680 0.1469 1.0000
8.250 1.3004 0.01329 0.00707 -0.0649 0.1374 1.0000
8.500 1.3062 0.01378 0.00743 -0.0608 0.1155 1.0000
8.750 1.2997 0.01480 0.00820 -0.0546 0.0763 1.0000
9.000 1.2967 0.01580 0.00903 -0.0492 0.0435 1.0000
9.250 1.3038 0.01645 0.00964 -0.0457 0.0347 1.0000
9.500 1.3144 0.01697 0.01020 -0.0429 0.0324 1.0000
9.750 1.3251 0.01752 0.01077 -0.0402 0.0309 1.0000
10.000 1.3354 0.01811 0.01141 -0.0375 0.0289 1.0000
10.250 1.3473 0.01865 0.01200 -0.0351 0.0281 1.0000
10.500 1.3592 0.01921 0.01261 -0.0328 0.0274 1.0000
10.750 1.3701 0.01984 0.01330 -0.0305 0.0266 1.0000
11.000 1.3801 0.02056 0.01407 -0.0281 0.0256 1.0000
11.250 1.3882 0.02141 0.01497 -0.0257 0.0246 1.0000
11.500 1.3905 0.02266 0.01630 -0.0226 0.0231 1.0000
11.750 1.3996 0.02355 0.01725 -0.0205 0.0226 1.0000
12.000 1.4110 0.02434 0.01810 -0.0189 0.0219 1.0000
12.250 1.4211 0.02525 0.01905 -0.0172 0.0211 1.0000
12.500 1.4299 0.02630 0.02015 -0.0156 0.0204 1.0000
12.750 1.4370 0.02753 0.02143 -0.0139 0.0196 1.0000
13.000 1.4398 0.02914 0.02310 -0.0121 0.0189 1.0000
13.250 1.4365 0.03134 0.02539 -0.0101 0.0181 1.0000
13.500 1.4457 0.03260 0.02672 -0.0090 0.0178 1.0000
13.750 1.4526 0.03408 0.02826 -0.0080 0.0172 1.0000
14.000 1.4607 0.03549 0.02972 -0.0071 0.0165 1.0000
14.250 1.4665 0.03717 0.03145 -0.0062 0.0160 1.0000
14.500 1.4692 0.03921 0.03353 -0.0054 0.0153 1.0000
14.750 1.4667 0.04186 0.03627 -0.0045 0.0149 1.0000
15.000 1.4563 0.04547 0.03998 -0.0038 0.0143 1.0000
15.250 1.4554 0.04818 0.04278 -0.0035 0.0142 1.0000
15.500 1.4591 0.05046 0.04514 -0.0033 0.0138 1.0000
15.750 1.4556 0.05365 0.04841 -0.0033 0.0134 1.0000
16.000 1.4560 0.05645 0.05129 -0.0034 0.0130 1.0000
16.250 1.4497 0.06024 0.05518 -0.0038 0.0128 1.0000
16.500 1.4467 0.06368 0.05869 -0.0043 0.0125 1.0000
16.750 1.4373 0.06809 0.06320 -0.0051 0.0124 1.0000
17.000 1.4308 0.07219 0.06738 -0.0059 0.0120 1.0000
17.250 1.4192 0.07706 0.07235 -0.0070 0.0118 1.0000
17.500 1.4010 0.08293 0.07831 -0.0085 0.0114 1.0000
17.750 1.3865 0.08829 0.08378 -0.0099 0.0114 1.0000
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