GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 500,000 Max Cl/Cd: 88.93 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe593-il-500000-n5.txt Download as CSV file: xf-goe593-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8704 0.04166 0.03876 -0.0850 1.0000 0.0117
-13.000 -0.8889 0.03647 0.03327 -0.0869 0.9961 0.0118
-12.750 -0.8762 0.03307 0.02962 -0.0896 0.9917 0.0120
-12.500 -0.8588 0.03060 0.02693 -0.0913 0.9877 0.0124
-12.250 -0.8380 0.02848 0.02458 -0.0929 0.9847 0.0128
-12.000 -0.8209 0.02675 0.02264 -0.0929 0.9794 0.0131
-11.750 -0.7980 0.02505 0.02070 -0.0938 0.9763 0.0135
-11.500 -0.7777 0.02376 0.01926 -0.0937 0.9715 0.0140
-11.250 -0.7532 0.02284 0.01825 -0.0940 0.9673 0.0144
-11.000 -0.7248 0.02208 0.01740 -0.0949 0.9648 0.0150
-10.750 -0.7021 0.02129 0.01651 -0.0945 0.9599 0.0155
-10.500 -0.6776 0.02048 0.01557 -0.0945 0.9553 0.0162
-10.250 -0.6503 0.01958 0.01447 -0.0950 0.9524 0.0169
-10.000 -0.6241 0.01895 0.01380 -0.0951 0.9484 0.0176
-9.750 -0.5980 0.01849 0.01327 -0.0951 0.9433 0.0181
-9.500 -0.5674 0.01795 0.01265 -0.0960 0.9402 0.0189
-9.250 -0.5349 0.01730 0.01187 -0.0973 0.9378 0.0198
-9.000 -0.5056 0.01674 0.01117 -0.0978 0.9334 0.0207
-8.750 -0.4751 0.01619 0.01057 -0.0987 0.9290 0.0215
-8.500 -0.4413 0.01580 0.01013 -0.1002 0.9253 0.0224
-8.250 -0.4065 0.01534 0.00958 -0.1019 0.9221 0.0234
-8.000 -0.3777 0.01488 0.00902 -0.1022 0.9162 0.0243
-7.750 -0.3453 0.01451 0.00852 -0.1033 0.9108 0.0252
-7.500 -0.3131 0.01390 0.00786 -0.1045 0.9059 0.0263
-7.250 -0.2867 0.01356 0.00746 -0.1043 0.8987 0.0272
-7.000 -0.2567 0.01322 0.00706 -0.1048 0.8925 0.0282
-6.750 -0.2293 0.01291 0.00667 -0.1047 0.8855 0.0292
-6.500 -0.2022 0.01261 0.00627 -0.1046 0.8780 0.0301
-6.250 -0.1751 0.01227 0.00585 -0.1044 0.8713 0.0309
-6.000 -0.1508 0.01185 0.00541 -0.1037 0.8631 0.0321
-5.750 -0.1241 0.01158 0.00508 -0.1035 0.8558 0.0331
-5.500 -0.0992 0.01131 0.00477 -0.1028 0.8473 0.0340
-5.250 -0.0729 0.01108 0.00447 -0.1024 0.8396 0.0352
-5.000 -0.0478 0.01087 0.00421 -0.1018 0.8306 0.0362
-4.750 -0.0220 0.01068 0.00393 -0.1012 0.8219 0.0370
-4.500 0.0027 0.01040 0.00361 -0.1005 0.8124 0.0384
-4.250 0.0278 0.01020 0.00337 -0.0998 0.8026 0.0399
-4.000 0.0533 0.01004 0.00315 -0.0992 0.7928 0.0417
-3.750 0.0783 0.00990 0.00296 -0.0985 0.7813 0.0437
-3.500 0.1032 0.00977 0.00277 -0.0978 0.7690 0.0462
-3.250 0.1274 0.00964 0.00258 -0.0969 0.7541 0.0504
-3.000 0.1515 0.00954 0.00242 -0.0959 0.7386 0.0564
-2.750 0.1755 0.00942 0.00230 -0.0950 0.7247 0.0686
-2.500 0.1999 0.00932 0.00221 -0.0942 0.7134 0.0885
-2.250 0.2248 0.00925 0.00214 -0.0935 0.7025 0.1041
-2.000 0.2498 0.00919 0.00207 -0.0928 0.6923 0.1168
-1.750 0.2745 0.00915 0.00201 -0.0921 0.6820 0.1278
-1.500 0.2995 0.00911 0.00195 -0.0914 0.6710 0.1387
-1.250 0.3243 0.00908 0.00190 -0.0907 0.6601 0.1513
-1.000 0.3483 0.00901 0.00187 -0.0898 0.6484 0.1729
-0.750 0.3714 0.00881 0.00186 -0.0889 0.6381 0.2404
-0.500 0.3943 0.00861 0.00184 -0.0879 0.6279 0.3136
-0.250 0.4152 0.00832 0.00184 -0.0866 0.6173 0.4199
0.000 0.4367 0.00809 0.00186 -0.0853 0.6065 0.5197
0.250 0.4573 0.00789 0.00189 -0.0837 0.5958 0.6072
0.500 0.4755 0.00764 0.00193 -0.0816 0.5857 0.7127
0.750 0.4948 0.00742 0.00202 -0.0794 0.5744 0.8177
1.000 0.5394 0.00743 0.00219 -0.0828 0.5582 0.9182
1.250 0.5955 0.00766 0.00232 -0.0890 0.5383 0.9543
1.500 0.6358 0.00785 0.00241 -0.0917 0.5189 0.9704
1.750 0.6702 0.00806 0.00251 -0.0932 0.4983 0.9821
2.000 0.7112 0.00832 0.00264 -0.0961 0.4752 0.9932
2.250 0.7538 0.00858 0.00276 -0.0996 0.4506 1.0000
2.500 0.7711 0.00880 0.00287 -0.0974 0.4302 1.0000
3.000 0.8073 0.00922 0.00310 -0.0934 0.3968 1.0000
3.250 0.8263 0.00941 0.00322 -0.0917 0.3830 1.0000
3.500 0.8456 0.00960 0.00335 -0.0899 0.3704 1.0000
3.750 0.8649 0.00980 0.00349 -0.0882 0.3589 1.0000
4.000 0.8841 0.01000 0.00364 -0.0864 0.3485 1.0000
4.250 0.9039 0.01019 0.00380 -0.0848 0.3384 1.0000
4.500 0.9234 0.01040 0.00396 -0.0832 0.3290 1.0000
4.750 0.9428 0.01061 0.00413 -0.0815 0.3199 1.0000
5.000 0.9622 0.01082 0.00431 -0.0798 0.3096 1.0000
5.250 0.9810 0.01106 0.00451 -0.0780 0.3009 1.0000
5.500 1.0003 0.01128 0.00470 -0.0764 0.2914 1.0000
5.750 1.0191 0.01152 0.00491 -0.0746 0.2827 1.0000
6.000 1.0377 0.01174 0.00512 -0.0728 0.2749 1.0000
6.250 1.0552 0.01197 0.00533 -0.0709 0.2680 1.0000
6.500 1.0734 0.01218 0.00554 -0.0690 0.2619 1.0000
6.750 1.0901 0.01244 0.00579 -0.0669 0.2551 1.0000
7.000 1.1088 0.01266 0.00602 -0.0652 0.2479 1.0000
7.250 1.1258 0.01296 0.00629 -0.0632 0.2408 1.0000
7.500 1.1446 0.01320 0.00655 -0.0616 0.2336 1.0000
8.000 1.1797 0.01382 0.00715 -0.0581 0.2167 1.0000
8.500 1.2153 0.01447 0.00781 -0.0547 0.2027 1.0000
8.750 1.2318 0.01486 0.00819 -0.0529 0.1938 1.0000
9.000 1.2484 0.01527 0.00858 -0.0512 0.1828 1.0000
9.250 1.2643 0.01572 0.00901 -0.0494 0.1703 1.0000
9.500 1.2772 0.01632 0.00954 -0.0472 0.1523 1.0000
9.750 1.2848 0.01725 0.01030 -0.0444 0.1227 1.0000
10.000 1.2903 0.01833 0.01123 -0.0413 0.0962 1.0000
10.250 1.2978 0.01933 0.01214 -0.0387 0.0796 1.0000
10.500 1.3078 0.02022 0.01299 -0.0365 0.0703 1.0000
10.750 1.3187 0.02107 0.01384 -0.0345 0.0639 1.0000
11.000 1.3300 0.02192 0.01471 -0.0327 0.0593 1.0000
11.250 1.3409 0.02282 0.01563 -0.0309 0.0560 1.0000
11.500 1.3537 0.02362 0.01650 -0.0294 0.0534 1.0000
11.750 1.3654 0.02451 0.01744 -0.0279 0.0510 1.0000
12.000 1.3757 0.02552 0.01848 -0.0263 0.0486 1.0000
12.250 1.3842 0.02670 0.01969 -0.0246 0.0458 1.0000
12.500 1.3959 0.02767 0.02075 -0.0234 0.0443 1.0000
12.750 1.4061 0.02878 0.02192 -0.0221 0.0421 1.0000
13.000 1.4144 0.03006 0.02324 -0.0208 0.0397 1.0000
13.250 1.4216 0.03149 0.02472 -0.0195 0.0376 1.0000
13.500 1.4304 0.03282 0.02612 -0.0184 0.0354 1.0000
13.750 1.4369 0.03438 0.02774 -0.0173 0.0328 1.0000
14.000 1.4424 0.03609 0.02950 -0.0163 0.0303 1.0000
14.250 1.4470 0.03793 0.03138 -0.0154 0.0272 1.0000
14.500 1.4501 0.03997 0.03348 -0.0145 0.0247 1.0000
15.000 1.4513 0.04480 0.03841 -0.0132 0.0192 1.0000
15.250 1.4494 0.04759 0.04125 -0.0128 0.0175 1.0000
15.500 1.4482 0.05040 0.04415 -0.0125 0.0164 1.0000
15.750 1.4454 0.05350 0.04734 -0.0124 0.0153 1.0000
16.000 1.4404 0.05695 0.05087 -0.0125 0.0144 1.0000
16.250 1.4354 0.06050 0.05453 -0.0127 0.0137 1.0000
16.500 1.4304 0.06416 0.05829 -0.0131 0.0131 1.0000
16.750 1.4250 0.06796 0.06221 -0.0137 0.0127 1.0000
17.000 1.4174 0.07217 0.06653 -0.0146 0.0123 1.0000
17.250 1.4086 0.07662 0.07108 -0.0155 0.0120 1.0000
17.500 1.3987 0.08133 0.07590 -0.0167 0.0117 1.0000
17.750 1.3871 0.08640 0.08109 -0.0182 0.0113 1.0000
18.000 1.3748 0.09165 0.08644 -0.0197 0.0110 1.0000
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