Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.4 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin2-il-1000000.txt Download as CSV file: xf-glennmartin2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 2
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.2490 0.15408 0.15241 -0.0416 0.9964 0.0116
-14.750 -0.2356 0.15060 0.14893 -0.0446 0.9955 0.0121
-13.000 -0.6447 0.02855 0.02578 -0.1230 0.9625 0.0123
-12.750 -0.6248 0.02562 0.02262 -0.1245 0.9602 0.0126
-12.500 -0.6000 0.02369 0.02050 -0.1258 0.9585 0.0130
-12.250 -0.5833 0.02224 0.01888 -0.1248 0.9528 0.0132
-12.000 -0.5586 0.02093 0.01739 -0.1252 0.9486 0.0135
-11.750 -0.5290 0.01950 0.01577 -0.1266 0.9458 0.0139
-11.500 -0.5056 0.01814 0.01426 -0.1267 0.9406 0.0145
-11.250 -0.4806 0.01750 0.01355 -0.1263 0.9345 0.0149
-11.000 -0.4476 0.01687 0.01284 -0.1276 0.9303 0.0154
-10.750 -0.4240 0.01631 0.01218 -0.1269 0.9235 0.0159
-10.500 -0.3958 0.01589 0.01167 -0.1270 0.9176 0.0164
-10.250 -0.3674 0.01549 0.01113 -0.1271 0.9111 0.0169
-10.000 -0.3498 0.01457 0.01008 -0.1253 0.9024 0.0176
-9.750 -0.3253 0.01412 0.00955 -0.1246 0.8957 0.0182
-9.500 -0.3025 0.01385 0.00923 -0.1234 0.8888 0.0188
-9.250 -0.2755 0.01358 0.00889 -0.1231 0.8828 0.0196
-9.000 -0.2543 0.01326 0.00850 -0.1216 0.8759 0.0202
-8.750 -0.2292 0.01303 0.00815 -0.1208 0.8688 0.0207
-8.500 -0.2104 0.01236 0.00739 -0.1189 0.8612 0.0218
-8.250 -0.1868 0.01210 0.00708 -0.1179 0.8525 0.0225
-8.000 -0.1633 0.01193 0.00688 -0.1168 0.8446 0.0234
-7.750 -0.1392 0.01173 0.00659 -0.1158 0.8361 0.0244
-7.500 -0.1157 0.01160 0.00639 -0.1146 0.8263 0.0251
-7.250 -0.0952 0.01109 0.00577 -0.1130 0.8154 0.0262
-7.000 -0.0738 0.01081 0.00542 -0.1114 0.8022 0.0272
-6.750 -0.0520 0.01064 0.00519 -0.1099 0.7865 0.0282
-6.500 -0.0310 0.01052 0.00497 -0.1082 0.7654 0.0293
-6.250 -0.0123 0.01048 0.00477 -0.1060 0.7355 0.0302
-6.000 0.0025 0.01054 0.00462 -0.1030 0.6935 0.0306
-5.750 0.0180 0.01022 0.00413 -0.1003 0.6673 0.0322
-5.500 0.0383 0.01011 0.00393 -0.0985 0.6516 0.0335
-5.250 0.0605 0.01003 0.00378 -0.0971 0.6405 0.0349
-5.000 0.0824 0.00995 0.00362 -0.0957 0.6298 0.0360
-4.750 0.1056 0.00987 0.00347 -0.0945 0.6205 0.0369
-4.500 0.1273 0.00965 0.00319 -0.0930 0.6123 0.0393
-4.250 0.1504 0.00953 0.00305 -0.0919 0.6035 0.0413
-4.000 0.1734 0.00946 0.00293 -0.0907 0.5953 0.0432
-3.750 0.1963 0.00934 0.00277 -0.0894 0.5860 0.0466
-3.500 0.2191 0.00926 0.00269 -0.0882 0.5761 0.0510
-3.250 0.2409 0.00919 0.00261 -0.0868 0.5633 0.0576
-3.000 0.2628 0.00922 0.00259 -0.0853 0.5445 0.0634
-2.750 0.2780 0.00933 0.00254 -0.0826 0.4958 0.0703
-2.500 0.2877 0.00977 0.00265 -0.0788 0.4262 0.0740
-2.250 0.3063 0.00996 0.00270 -0.0768 0.4013 0.0766
-2.000 0.3249 0.00998 0.00266 -0.0747 0.3860 0.0819
-1.750 0.3441 0.01003 0.00265 -0.0728 0.3749 0.0854
-1.500 0.3644 0.01007 0.00264 -0.0712 0.3663 0.0880
-1.250 0.3844 0.01013 0.00264 -0.0694 0.3589 0.0896
-1.000 0.4048 0.01009 0.00259 -0.0678 0.3539 0.0950
-0.750 0.4249 0.01010 0.00258 -0.0661 0.3488 0.0998
-0.500 0.4448 0.01015 0.00259 -0.0644 0.3435 0.1037
-0.250 0.4659 0.01011 0.00258 -0.0629 0.3407 0.1137
0.000 0.4843 0.01000 0.00261 -0.0610 0.3377 0.1608
0.250 0.5038 0.01000 0.00272 -0.0592 0.3341 0.2139
0.500 0.5245 0.01009 0.00282 -0.0578 0.3308 0.2306
0.750 0.5447 0.01020 0.00293 -0.0562 0.3273 0.2430
1.000 0.5674 0.01025 0.00299 -0.0551 0.3257 0.2513
1.250 0.5897 0.01031 0.00307 -0.0540 0.3236 0.2591
1.500 0.6114 0.01039 0.00314 -0.0528 0.3212 0.2649
1.750 0.6326 0.01048 0.00323 -0.0514 0.3192 0.2713
2.000 0.6535 0.01059 0.00333 -0.0501 0.3167 0.2767
2.250 0.6735 0.01072 0.00344 -0.0486 0.3140 0.2829
2.500 0.6932 0.01087 0.00359 -0.0471 0.3114 0.2907
2.750 0.7152 0.01093 0.00368 -0.0460 0.3105 0.2982
3.000 0.7369 0.01099 0.00378 -0.0448 0.3092 0.3067
3.250 0.7582 0.01104 0.00388 -0.0437 0.3074 0.3212
3.500 0.7776 0.01104 0.00402 -0.0421 0.3061 0.3697
3.750 1.0072 0.01083 0.00516 -0.0879 0.2980 0.9954
4.000 1.0550 0.01106 0.00536 -0.0928 0.2954 0.9982
4.250 1.1012 0.01116 0.00546 -0.0971 0.2940 1.0000
4.500 1.1170 0.01124 0.00555 -0.0948 0.2928 1.0000
4.750 1.1337 0.01131 0.00562 -0.0928 0.2903 1.0000
5.000 1.1499 0.01143 0.00575 -0.0906 0.2889 1.0000
5.250 1.1663 0.01155 0.00585 -0.0885 0.2857 1.0000
5.500 1.1814 0.01173 0.00601 -0.0862 0.2832 1.0000
5.750 1.1955 0.01197 0.00624 -0.0838 0.2802 1.0000
6.000 1.2155 0.01203 0.00633 -0.0825 0.2785 1.0000
6.250 1.2352 0.01211 0.00643 -0.0811 0.2757 1.0000
6.500 1.2533 0.01224 0.00658 -0.0795 0.2731 1.0000
6.750 1.2699 0.01244 0.00674 -0.0777 0.2680 1.0000
7.000 1.2867 0.01265 0.00695 -0.0759 0.2645 1.0000
7.250 1.3066 0.01277 0.00710 -0.0747 0.2618 1.0000
7.500 1.3250 0.01294 0.00728 -0.0733 0.2569 1.0000
7.750 1.3413 0.01321 0.00750 -0.0715 0.2495 1.0000
8.000 1.3590 0.01344 0.00771 -0.0701 0.2399 1.0000
8.250 1.3724 0.01385 0.00803 -0.0679 0.2239 1.0000
8.500 1.3692 0.01504 0.00889 -0.0631 0.1765 1.0000
8.750 1.3635 0.01645 0.01003 -0.0582 0.1401 1.0000
9.000 1.3615 0.01775 0.01113 -0.0540 0.1089 1.0000
9.250 1.3325 0.02060 0.01358 -0.0463 0.0417 1.0000
9.500 1.3297 0.02214 0.01507 -0.0425 0.0165 1.0000
9.750 1.3397 0.02298 0.01595 -0.0406 0.0151 1.0000
10.000 1.3492 0.02388 0.01691 -0.0387 0.0140 1.0000
10.250 1.3594 0.02476 0.01784 -0.0370 0.0134 1.0000
10.500 1.3686 0.02574 0.01888 -0.0353 0.0129 1.0000
10.750 1.3763 0.02686 0.02005 -0.0336 0.0124 1.0000
11.000 1.3826 0.02811 0.02137 -0.0318 0.0120 1.0000
11.250 1.3849 0.02971 0.02304 -0.0298 0.0113 1.0000
11.500 1.3854 0.03154 0.02497 -0.0278 0.0109 1.0000
11.750 1.3937 0.03281 0.02629 -0.0267 0.0105 1.0000
12.000 1.3973 0.03454 0.02809 -0.0253 0.0104 1.0000
12.250 1.4012 0.03633 0.02995 -0.0242 0.0100 1.0000
12.500 1.4033 0.03837 0.03206 -0.0231 0.0097 1.0000
12.750 1.4029 0.04076 0.03453 -0.0221 0.0094 1.0000
13.000 1.4021 0.04328 0.03714 -0.0213 0.0092 1.0000
13.250 1.3987 0.04622 0.04016 -0.0207 0.0091 1.0000
13.500 1.3934 0.04944 0.04348 -0.0202 0.0090 1.0000
13.750 1.3830 0.05333 0.04749 -0.0198 0.0087 1.0000
14.000 1.3745 0.05713 0.05139 -0.0196 0.0087 1.0000
14.250 1.3521 0.06283 0.05725 -0.0197 0.0085 1.0000
14.500 1.3393 0.06753 0.06206 -0.0201 0.0085 1.0000
14.750 1.3205 0.07327 0.06794 -0.0209 0.0085 1.0000
15.000 1.3138 0.07746 0.07222 -0.0216 0.0083 1.0000
15.250 1.2865 0.08476 0.07967 -0.0229 0.0084 1.0000
15.500 1.2875 0.08788 0.08286 -0.0235 0.0082 1.0000
15.750 1.2703 0.09373 0.08881 -0.0247 0.0082 1.0000
16.000 1.2622 0.09826 0.09343 -0.0257 0.0080 1.0000
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Polar data table (+)
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