Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 500,000 Max Cl/Cd: 90.12 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg2-il-500000-n5.txt Download as CSV file: xf-fg2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 2
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4223 0.08662 0.08450 -0.0181 1.0000 0.0065
-8.000 -0.4287 0.08394 0.08186 -0.0180 1.0000 0.0069
-7.750 -0.4403 0.08106 0.07902 -0.0173 1.0000 0.0066
-7.500 -0.4423 0.07753 0.07551 -0.0185 1.0000 0.0068
-7.250 -0.4246 0.07158 0.06953 -0.0261 0.9973 0.0071
-7.000 -0.4018 0.06501 0.06289 -0.0345 0.9935 0.0071
-6.750 -0.3785 0.05593 0.05366 -0.0438 0.9883 0.0081
-6.500 -0.3572 0.04989 0.04746 -0.0485 0.9829 0.0085
-6.000 -0.3119 0.04240 0.03967 -0.0527 0.9712 0.0092
-5.750 -0.2937 0.03823 0.03529 -0.0529 0.9617 0.0097
-5.500 -0.2828 0.03085 0.02743 -0.0512 0.9492 0.0112
-5.250 -0.2619 0.02804 0.02439 -0.0505 0.9389 0.0120
-5.000 -0.2347 0.02630 0.02247 -0.0509 0.9304 0.0126
-4.750 -0.2136 0.01984 0.01521 -0.0488 0.9224 0.0157
-4.500 -0.1747 0.01902 0.01426 -0.0516 0.9150 0.0165
-4.250 -0.1289 0.01837 0.01347 -0.0559 0.9056 0.0174
-4.000 -0.0721 0.01673 0.01148 -0.0624 0.8928 0.0198
-3.750 -0.0213 0.01574 0.01001 -0.0670 0.8723 0.0217
-3.500 0.0108 0.01416 0.00818 -0.0683 0.8477 0.0229
-3.250 0.0398 0.01381 0.00770 -0.0687 0.8152 0.0240
-2.750 0.0848 0.01302 0.00634 -0.0660 0.7198 0.0254
-2.250 0.1274 0.01236 0.00520 -0.0629 0.6495 0.0263
-2.000 0.1503 0.01211 0.00479 -0.0618 0.6256 0.0271
-1.750 0.1734 0.01178 0.00432 -0.0606 0.6054 0.0274
-1.500 0.1969 0.01146 0.00388 -0.0596 0.5886 0.0277
-1.250 0.2206 0.01121 0.00354 -0.0586 0.5739 0.0282
-1.000 0.2443 0.01100 0.00325 -0.0577 0.5603 0.0286
-0.750 0.2681 0.01087 0.00304 -0.0567 0.5474 0.0291
-0.500 0.2920 0.01073 0.00285 -0.0558 0.5348 0.0294
-0.250 0.3159 0.01060 0.00268 -0.0549 0.5225 0.0297
0.000 0.3388 0.01038 0.00240 -0.0538 0.5098 0.0300
0.250 0.3617 0.01022 0.00218 -0.0528 0.4957 0.0306
0.500 0.3847 0.01011 0.00200 -0.0517 0.4790 0.0317
0.750 0.4082 0.01008 0.00191 -0.0508 0.4611 0.0317
1.000 0.4318 0.01009 0.00184 -0.0499 0.4415 0.0317
1.250 0.4556 0.01012 0.00178 -0.0490 0.4223 0.0318
1.500 0.4796 0.01016 0.00174 -0.0482 0.4056 0.0320
1.750 0.5033 0.01023 0.00174 -0.0473 0.3877 0.0323
2.000 0.5274 0.01030 0.00174 -0.0465 0.3740 0.0331
2.250 0.5516 0.01039 0.00177 -0.0458 0.3611 0.0336
2.500 0.5759 0.01047 0.00182 -0.0451 0.3506 0.0351
2.750 0.6001 0.01057 0.00188 -0.0443 0.3418 0.0375
3.000 0.6248 0.01063 0.00196 -0.0437 0.3344 0.0489
3.500 0.8095 0.00942 0.00283 -0.0747 0.3066 1.0000
3.750 0.8331 0.00958 0.00297 -0.0738 0.2997 1.0000
4.000 0.8570 0.00971 0.00311 -0.0731 0.2935 1.0000
4.250 0.8804 0.00987 0.00326 -0.0722 0.2846 1.0000
4.500 0.9036 0.01006 0.00342 -0.0713 0.2704 1.0000
4.750 0.9264 0.01028 0.00359 -0.0704 0.2529 1.0000
5.000 0.9481 0.01058 0.00378 -0.0693 0.2224 1.0000
5.250 0.9633 0.01143 0.00422 -0.0672 0.1522 1.0000
5.500 0.9826 0.01195 0.00462 -0.0657 0.1277 1.0000
5.750 1.0033 0.01234 0.00494 -0.0644 0.1117 1.0000
6.000 1.0236 0.01276 0.00528 -0.0631 0.0909 1.0000
6.250 1.0337 0.01404 0.00613 -0.0600 0.0213 1.0000
6.500 1.0539 0.01445 0.00657 -0.0586 0.0147 1.0000
6.750 1.0741 0.01486 0.00707 -0.0573 0.0128 1.0000
7.000 1.0934 0.01533 0.00762 -0.0557 0.0113 1.0000
7.250 1.1108 0.01597 0.00838 -0.0538 0.0096 1.0000
7.500 1.1304 0.01638 0.00885 -0.0524 0.0090 1.0000
7.750 1.1485 0.01690 0.00946 -0.0507 0.0083 1.0000
8.000 1.1657 0.01747 0.01012 -0.0488 0.0077 1.0000
8.250 1.1821 0.01809 0.01081 -0.0469 0.0072 1.0000
8.500 1.1956 0.01888 0.01169 -0.0445 0.0067 1.0000
8.750 1.2051 0.01992 0.01283 -0.0414 0.0063 1.0000
9.000 1.2176 0.02070 0.01371 -0.0389 0.0062 1.0000
9.250 1.2332 0.02124 0.01432 -0.0370 0.0057 1.0000
9.500 1.2424 0.02212 0.01530 -0.0339 0.0054 1.0000
9.750 1.2506 0.02283 0.01611 -0.0307 0.0051 1.0000
10.000 1.2535 0.02379 0.01717 -0.0266 0.0050 1.0000
10.250 1.2596 0.02465 0.01811 -0.0233 0.0048 1.0000
10.500 1.2657 0.02557 0.01911 -0.0203 0.0047 1.0000
10.750 1.2681 0.02676 0.02040 -0.0169 0.0045 1.0000
11.000 1.2687 0.02814 0.02186 -0.0137 0.0043 1.0000
11.250 1.2691 0.02966 0.02350 -0.0107 0.0043 1.0000
11.500 1.2618 0.03192 0.02586 -0.0076 0.0041 1.0000
11.750 1.2623 0.03376 0.02784 -0.0056 0.0041 1.0000
12.000 1.2588 0.03613 0.03033 -0.0038 0.0041 1.0000
12.250 1.2593 0.03835 0.03270 -0.0027 0.0040 1.0000
12.500 1.2568 0.04106 0.03555 -0.0019 0.0039 1.0000
12.750 1.2542 0.04397 0.03862 -0.0015 0.0039 1.0000
13.000 1.2503 0.04726 0.04206 -0.0015 0.0038 1.0000
13.250 1.2454 0.05081 0.04576 -0.0018 0.0037 1.0000
13.500 1.2391 0.05467 0.04977 -0.0022 0.0037 1.0000
13.750 1.2331 0.05861 0.05387 -0.0030 0.0036 1.0000
14.000 1.2285 0.06249 0.05788 -0.0042 0.0035 1.0000
14.250 1.2177 0.06722 0.06276 -0.0052 0.0035 1.0000
14.500 1.2081 0.07197 0.06767 -0.0066 0.0035 1.0000
14.750 1.1985 0.07685 0.07269 -0.0082 0.0035 1.0000
15.000 1.1869 0.08224 0.07822 -0.0101 0.0035 1.0000
15.250 1.1795 0.08718 0.08329 -0.0123 0.0034 1.0000
15.500 1.1776 0.09149 0.08767 -0.0149 0.0031 1.0000
15.750 1.1554 0.09904 0.09543 -0.0174 0.0033 1.0000
16.000 1.1378 0.10623 0.10279 -0.0204 0.0035 1.0000
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Polar data table (+)
Polar graphs
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