Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 500,000 Max Cl/Cd: 64.89 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin4-il-500000.txt Download as CSV file: xf-glennmartin4-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 4
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2232 0.09396 0.09185 -0.0703 0.9593 0.0270
-8.750 -0.2078 0.09033 0.08822 -0.0743 0.9576 0.0273
-8.500 -0.2016 0.08679 0.08468 -0.0760 0.9513 0.0277
-8.250 -0.1908 0.08375 0.08164 -0.0790 0.9491 0.0286
-7.750 -0.3745 0.04432 0.04133 -0.0815 0.9238 0.0219
-7.500 -0.3714 0.04135 0.03822 -0.0791 0.9179 0.0223
-7.250 -0.3102 0.04650 0.04358 -0.0834 0.9171 0.0267
-7.000 -0.2935 0.04374 0.04072 -0.0836 0.9150 0.0271
-6.750 -0.2880 0.04220 0.03912 -0.0803 0.9058 0.0274
-6.500 -0.3559 0.02743 0.02287 -0.0647 0.8968 0.0236
-6.250 -0.3359 0.02568 0.02087 -0.0630 0.8918 0.0248
-6.000 -0.3097 0.02414 0.01892 -0.0622 0.8893 0.0263
-5.750 -0.3010 0.02229 0.01674 -0.0581 0.8804 0.0267
-5.500 -0.2773 0.02051 0.01486 -0.0572 0.8763 0.0277
-5.250 -0.2476 0.01948 0.01373 -0.0573 0.8735 0.0286
-5.000 -0.2335 0.01901 0.01320 -0.0542 0.8628 0.0298
-4.750 -0.2016 0.01790 0.01191 -0.0546 0.8588 0.0309
-4.500 -0.1795 0.01729 0.01117 -0.0531 0.8480 0.0316
-4.250 -0.1430 0.01586 0.00962 -0.0547 0.8419 0.0336
-4.000 -0.1072 0.01519 0.00890 -0.0562 0.8303 0.0360
-3.750 -0.0618 0.01431 0.00788 -0.0596 0.8156 0.0372
-3.500 -0.0135 0.01341 0.00682 -0.0638 0.7972 0.0393
-3.250 0.0239 0.01285 0.00613 -0.0657 0.7682 0.0413
-3.000 0.0518 0.01270 0.00579 -0.0656 0.7316 0.0435
-2.750 0.0672 0.01271 0.00555 -0.0628 0.6863 0.0449
-2.500 0.0791 0.01275 0.00534 -0.0592 0.6496 0.0460
-2.250 0.0956 0.01269 0.00518 -0.0568 0.6282 0.0483
-2.000 0.1138 0.01271 0.00510 -0.0547 0.6089 0.0511
-1.750 0.1335 0.01272 0.00500 -0.0529 0.5937 0.0549
-1.500 0.1546 0.01279 0.00503 -0.0515 0.5812 0.0615
-1.250 0.1764 0.01276 0.00497 -0.0502 0.5698 0.0690
-1.000 0.1985 0.01274 0.00490 -0.0490 0.5593 0.0809
-0.750 0.2199 0.01277 0.00485 -0.0477 0.5480 0.0872
-0.500 0.2433 0.01272 0.00477 -0.0469 0.5393 0.0938
-0.250 0.2662 0.01274 0.00473 -0.0460 0.5305 0.0986
0.000 0.2897 0.01274 0.00470 -0.0452 0.5211 0.1043
0.250 0.3131 0.01276 0.00470 -0.0445 0.5121 0.1125
0.500 0.3372 0.01277 0.00472 -0.0438 0.5029 0.1225
0.750 0.3613 0.01280 0.00476 -0.0432 0.4940 0.1387
1.000 0.3909 0.01263 0.00481 -0.0441 0.4842 0.2224
1.250 0.6926 0.01294 0.00699 -0.1070 0.4458 0.9994
1.500 0.7163 0.01308 0.00704 -0.1065 0.4338 1.0000
1.750 0.7341 0.01321 0.00708 -0.1046 0.4222 1.0000
2.000 0.7516 0.01338 0.00715 -0.1028 0.4116 1.0000
2.250 0.7695 0.01355 0.00723 -0.1009 0.4007 1.0000
2.500 0.7886 0.01371 0.00732 -0.0994 0.3920 1.0000
2.750 0.8071 0.01392 0.00744 -0.0978 0.3842 1.0000
3.000 0.8270 0.01408 0.00755 -0.0965 0.3776 1.0000
3.250 0.8461 0.01428 0.00768 -0.0950 0.3702 1.0000
3.500 0.8656 0.01449 0.00783 -0.0936 0.3651 1.0000
3.750 0.8861 0.01465 0.00797 -0.0924 0.3599 1.0000
4.000 0.9056 0.01486 0.00813 -0.0911 0.3548 1.0000
4.250 0.9247 0.01513 0.00832 -0.0896 0.3504 1.0000
4.500 0.9455 0.01528 0.00849 -0.0886 0.3462 1.0000
4.750 0.9658 0.01548 0.00868 -0.0874 0.3433 1.0000
5.000 0.9848 0.01572 0.00888 -0.0860 0.3389 1.0000
5.250 1.0041 0.01599 0.00911 -0.0847 0.3356 1.0000
5.500 1.0245 0.01622 0.00934 -0.0837 0.3325 1.0000
5.750 1.0451 0.01641 0.00956 -0.0826 0.3301 1.0000
6.000 1.0653 0.01663 0.00978 -0.0816 0.3273 1.0000
6.250 1.0849 0.01688 0.01003 -0.0804 0.3241 1.0000
6.500 1.1041 0.01717 0.01029 -0.0792 0.3209 1.0000
6.750 1.1238 0.01747 0.01058 -0.0781 0.3174 1.0000
7.000 1.1439 0.01770 0.01086 -0.0771 0.3157 1.0000
7.250 1.1630 0.01795 0.01114 -0.0759 0.3129 1.0000
7.500 1.1816 0.01821 0.01143 -0.0747 0.3101 1.0000
7.750 1.2003 0.01851 0.01173 -0.0735 0.3074 1.0000
8.000 1.2178 0.01892 0.01209 -0.0721 0.3023 1.0000
8.250 1.2353 0.01917 0.01242 -0.0707 0.2996 1.0000
8.500 1.2523 0.01945 0.01275 -0.0693 0.2959 1.0000
8.750 1.2695 0.01977 0.01311 -0.0679 0.2929 1.0000
9.000 1.2845 0.02020 0.01351 -0.0662 0.2884 1.0000
9.250 1.3017 0.02056 0.01392 -0.0649 0.2853 1.0000
9.500 1.3178 0.02087 0.01431 -0.0634 0.2811 1.0000
9.750 1.3335 0.02125 0.01473 -0.0619 0.2771 1.0000
10.000 1.3453 0.02181 0.01526 -0.0598 0.2708 1.0000
10.250 1.3627 0.02217 0.01571 -0.0586 0.2688 1.0000
10.500 1.3776 0.02258 0.01618 -0.0571 0.2612 1.0000
10.750 1.3898 0.02315 0.01674 -0.0553 0.2518 1.0000
11.000 1.4015 0.02378 0.01738 -0.0534 0.2428 1.0000
11.250 1.4111 0.02455 0.01812 -0.0513 0.2278 1.0000
11.500 1.4172 0.02556 0.01906 -0.0487 0.2078 1.0000
11.750 1.4111 0.02731 0.02063 -0.0448 0.1767 1.0000
12.000 1.3904 0.03008 0.02315 -0.0393 0.1389 1.0000
12.250 1.3691 0.03311 0.02601 -0.0343 0.1078 1.0000
12.500 1.3204 0.03856 0.03123 -0.0276 0.0484 1.0000
12.750 1.3113 0.04133 0.03406 -0.0252 0.0367 1.0000
13.000 1.3036 0.04415 0.03694 -0.0233 0.0296 1.0000
13.250 1.2970 0.04706 0.03992 -0.0217 0.0255 1.0000
13.500 1.2927 0.04988 0.04285 -0.0206 0.0236 1.0000
13.750 1.2853 0.05314 0.04622 -0.0197 0.0222 1.0000
14.000 1.2773 0.05658 0.04977 -0.0191 0.0213 1.0000
14.250 1.2685 0.06023 0.05355 -0.0186 0.0206 1.0000
14.500 1.2591 0.06403 0.05748 -0.0183 0.0201 1.0000
14.750 1.2498 0.06791 0.06148 -0.0181 0.0199 1.0000
15.000 1.2382 0.07211 0.06579 -0.0181 0.0191 1.0000
15.250 1.2263 0.07641 0.07022 -0.0182 0.0188 1.0000
15.500 1.2147 0.08074 0.07465 -0.0184 0.0184 1.0000
15.750 1.2008 0.08553 0.07956 -0.0188 0.0185 1.0000
16.000 1.1797 0.09135 0.08551 -0.0194 0.0178 1.0000
16.250 1.1709 0.09555 0.08981 -0.0200 0.0178 1.0000
16.500 1.1534 0.10106 0.09544 -0.0209 0.0176 1.0000
16.750 1.1339 0.10697 0.10146 -0.0219 0.0171 1.0000
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Polar data table (+)
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