GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 200,000 Max Cl/Cd: 75.77 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe391-il-200000-n5.txt Download as CSV file: xf-goe391-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4128 0.09032 0.08692 -0.0212 1.0000 0.0152
-7.250 -0.4177 0.08842 0.08508 -0.0195 1.0000 0.0172
-7.000 -0.4204 0.08601 0.08273 -0.0192 1.0000 0.0175
-6.750 -0.4216 0.08348 0.08023 -0.0193 1.0000 0.0179
-6.500 -0.4216 0.08088 0.07767 -0.0195 1.0000 0.0183
-6.250 -0.4198 0.07825 0.07506 -0.0200 1.0000 0.0185
-6.000 -0.4164 0.07538 0.07220 -0.0207 1.0000 0.0192
-5.750 -0.3898 0.07080 0.06756 -0.0273 0.9967 0.0209
-5.500 -0.3514 0.06632 0.06296 -0.0364 0.9929 0.0232
-5.250 -0.3184 0.06180 0.05831 -0.0428 0.9894 0.0234
-5.000 -0.2871 0.05732 0.05366 -0.0478 0.9866 0.0235
-4.500 -0.2293 0.04557 0.04154 -0.0551 0.9794 0.0125
-4.250 -0.2012 0.04109 0.03686 -0.0580 0.9761 0.0121
-3.750 -0.1410 0.03328 0.02852 -0.0624 0.9691 0.0146
-3.500 -0.1078 0.02939 0.02427 -0.0640 0.9657 0.0146
-3.250 -0.0775 0.02605 0.02054 -0.0646 0.9603 0.0147
-3.000 -0.0432 0.02323 0.01732 -0.0659 0.9570 0.0154
-2.750 -0.0082 0.02121 0.01493 -0.0674 0.9549 0.0180
-2.500 0.0171 0.01912 0.01241 -0.0663 0.9494 0.0202
-2.250 0.0485 0.01702 0.00977 -0.0662 0.9463 0.0229
-2.000 0.0807 0.01598 0.00854 -0.0672 0.9438 0.0273
-1.750 0.1144 0.01499 0.00731 -0.0683 0.9419 0.0315
-1.500 0.1415 0.01429 0.00648 -0.0681 0.9373 0.0365
-1.250 0.1709 0.01366 0.00580 -0.0684 0.9331 0.0393
-1.000 0.2050 0.01320 0.00528 -0.0697 0.9300 0.0431
-0.750 0.2375 0.01260 0.00463 -0.0706 0.9259 0.0430
-0.500 0.2651 0.01216 0.00417 -0.0704 0.9190 0.0432
-0.250 0.2990 0.01174 0.00371 -0.0716 0.9149 0.0439
0.000 0.3252 0.01149 0.00340 -0.0712 0.9070 0.0448
0.250 0.3574 0.01118 0.00306 -0.0719 0.9017 0.0486
0.750 0.4470 0.00862 0.00290 -0.0796 0.8904 1.0000
1.000 0.4766 0.00855 0.00276 -0.0797 0.8787 1.0000
1.250 0.5060 0.00849 0.00264 -0.0798 0.8663 1.0000
1.500 0.5350 0.00844 0.00256 -0.0797 0.8520 1.0000
1.750 0.5636 0.00840 0.00249 -0.0796 0.8357 1.0000
2.000 0.5921 0.00840 0.00246 -0.0795 0.8186 1.0000
2.250 0.6190 0.00840 0.00240 -0.0789 0.7847 1.0000
2.500 0.6448 0.00851 0.00225 -0.0779 0.7182 1.0000
2.750 0.6650 0.00893 0.00222 -0.0758 0.6293 1.0000
3.000 0.6833 0.00945 0.00238 -0.0737 0.5591 1.0000
3.250 0.7020 0.00996 0.00263 -0.0718 0.4920 1.0000
3.500 0.7184 0.01065 0.00290 -0.0696 0.3961 1.0000
3.750 0.7346 0.01148 0.00328 -0.0675 0.3124 1.0000
4.000 0.7544 0.01209 0.00365 -0.0662 0.2500 1.0000
4.250 0.7730 0.01288 0.00406 -0.0647 0.1714 1.0000
4.500 0.7929 0.01361 0.00459 -0.0634 0.1095 1.0000
4.750 0.8120 0.01449 0.00519 -0.0620 0.0591 1.0000
5.000 0.8340 0.01502 0.00575 -0.0610 0.0509 1.0000
5.250 0.8561 0.01556 0.00637 -0.0599 0.0472 1.0000
5.500 0.8770 0.01624 0.00720 -0.0586 0.0440 1.0000
5.750 0.8988 0.01677 0.00784 -0.0576 0.0391 1.0000
6.000 0.9174 0.01772 0.00885 -0.0562 0.0339 1.0000
6.250 0.9397 0.01823 0.00954 -0.0552 0.0289 1.0000
6.500 0.9587 0.01917 0.01053 -0.0538 0.0228 1.0000
6.750 0.9789 0.02006 0.01160 -0.0524 0.0179 1.0000
7.000 0.9994 0.02085 0.01250 -0.0512 0.0139 1.0000
7.250 1.0159 0.02255 0.01435 -0.0493 0.0122 1.0000
7.500 1.0346 0.02427 0.01628 -0.0476 0.0112 1.0000
7.750 1.0541 0.02577 0.01797 -0.0463 0.0099 1.0000
8.000 1.0730 0.02672 0.01905 -0.0451 0.0088 1.0000
8.250 1.0874 0.02956 0.02221 -0.0432 0.0079 1.0000
8.500 1.1024 0.03232 0.02538 -0.0412 0.0076 1.0000
8.750 1.1133 0.03559 0.02914 -0.0387 0.0073 1.0000
9.000 1.1193 0.03921 0.03326 -0.0358 0.0072 1.0000
9.250 1.1195 0.04321 0.03774 -0.0324 0.0071 1.0000
9.500 1.1150 0.04719 0.04214 -0.0288 0.0071 1.0000
9.750 1.1047 0.05126 0.04658 -0.0250 0.0070 1.0000
10.000 1.0884 0.05496 0.05056 -0.0208 0.0070 1.0000
10.250 1.0719 0.05844 0.05427 -0.0176 0.0071 1.0000
10.500 1.0533 0.06243 0.05847 -0.0157 0.0071 1.0000
10.750 1.0347 0.06681 0.06303 -0.0153 0.0071 1.0000
11.000 1.0150 0.07208 0.06847 -0.0166 0.0072 1.0000
11.250 0.9958 0.07844 0.07497 -0.0202 0.0072 1.0000
11.500 0.9762 0.08686 0.08352 -0.0263 0.0073 1.0000
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Polar data table (+)
Polar graphs
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