Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 500,000 Max Cl/Cd: 78.39 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin2-il-500000.txt Download as CSV file: xf-glennmartin2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1113 0.09728 0.09506 -0.0761 0.9741 0.0267
-10.500 -0.0951 0.09395 0.09173 -0.0795 0.9723 0.0281
-9.750 -0.3091 0.02904 0.02574 -0.1204 0.9359 0.0220
-9.500 -0.2826 0.02727 0.02380 -0.1217 0.9325 0.0227
-9.250 -0.2585 0.02467 0.02084 -0.1229 0.9292 0.0237
-9.000 -0.2503 0.02280 0.01862 -0.1200 0.9204 0.0245
-8.750 -0.2245 0.02137 0.01681 -0.1201 0.9158 0.0253
-8.500 -0.2096 0.01951 0.01477 -0.1184 0.9087 0.0265
-8.250 -0.1838 0.01907 0.01429 -0.1180 0.9027 0.0275
-8.000 -0.1520 0.01825 0.01330 -0.1190 0.8981 0.0289
-7.750 -0.1369 0.01755 0.01241 -0.1163 0.8893 0.0299
-7.500 -0.1098 0.01641 0.01098 -0.1161 0.8831 0.0310
-7.250 -0.0928 0.01561 0.01013 -0.1140 0.8744 0.0324
-7.000 -0.0630 0.01526 0.00970 -0.1142 0.8670 0.0340
-6.750 -0.0439 0.01482 0.00916 -0.1122 0.8567 0.0354
-6.500 -0.0181 0.01434 0.00852 -0.1115 0.8481 0.0366
-6.250 0.0036 0.01344 0.00748 -0.1102 0.8377 0.0382
-6.000 0.0259 0.01309 0.00710 -0.1088 0.8262 0.0398
-5.750 0.0498 0.01280 0.00673 -0.1077 0.8140 0.0415
-5.500 0.0732 0.01248 0.00629 -0.1065 0.8000 0.0431
-5.250 0.0961 0.01224 0.00593 -0.1052 0.7840 0.0445
-5.000 0.1166 0.01171 0.00532 -0.1035 0.7640 0.0468
-4.750 0.1375 0.01158 0.00507 -0.1017 0.7394 0.0490
-4.500 0.1571 0.01147 0.00480 -0.0997 0.7123 0.0510
-4.250 0.1768 0.01146 0.00461 -0.0977 0.6885 0.0530
-4.000 0.1958 0.01121 0.00428 -0.0957 0.6704 0.0565
-3.750 0.2172 0.01121 0.00419 -0.0941 0.6561 0.0603
-3.500 0.2389 0.01118 0.00404 -0.0927 0.6436 0.0640
-3.250 0.2599 0.01108 0.00391 -0.0911 0.6317 0.0706
-3.000 0.2822 0.01106 0.00381 -0.0898 0.6201 0.0769
-2.750 0.3031 0.01094 0.00367 -0.0882 0.6084 0.0844
-2.500 0.3244 0.01098 0.00362 -0.0867 0.5956 0.0893
-2.250 0.3430 0.01083 0.00343 -0.0846 0.5807 0.0957
-2.000 0.3616 0.01079 0.00334 -0.0826 0.5605 0.1011
-1.750 0.3763 0.01085 0.00325 -0.0796 0.5245 0.1047
-1.500 0.3783 0.01111 0.00319 -0.0742 0.4572 0.1091
-1.250 0.3869 0.01133 0.00322 -0.0702 0.4245 0.1141
-1.000 0.4018 0.01147 0.00324 -0.0675 0.4074 0.1200
-0.750 0.4184 0.01150 0.00326 -0.0651 0.3960 0.1335
-0.500 0.4349 0.01145 0.00339 -0.0628 0.3878 0.1900
-0.250 0.4543 0.01157 0.00353 -0.0610 0.3808 0.2318
0.000 0.4737 0.01174 0.00365 -0.0593 0.3751 0.2483
0.250 0.4953 0.01185 0.00374 -0.0580 0.3699 0.2610
0.500 0.5155 0.01196 0.00385 -0.0564 0.3654 0.2710
0.750 0.5354 0.01214 0.00396 -0.0549 0.3612 0.2801
1.000 0.5563 0.01224 0.00406 -0.0535 0.3578 0.2881
1.250 0.5778 0.01232 0.00414 -0.0522 0.3547 0.2960
1.500 0.5985 0.01241 0.00423 -0.0508 0.3516 0.3037
1.750 0.6190 0.01253 0.00433 -0.0494 0.3488 0.3112
2.000 0.6390 0.01267 0.00446 -0.0480 0.3458 0.3202
2.250 0.6595 0.01280 0.00460 -0.0466 0.3429 0.3331
2.500 0.6796 0.01279 0.00472 -0.0452 0.3408 0.3624
2.750 0.9618 0.01287 0.00613 -0.1017 0.3322 1.0000
3.000 0.9788 0.01307 0.00629 -0.0997 0.3302 1.0000
3.250 0.9972 0.01337 0.00653 -0.0981 0.3276 1.0000
3.500 1.0135 0.01348 0.00665 -0.0959 0.3264 1.0000
3.750 1.0283 0.01358 0.00676 -0.0934 0.3246 1.0000
4.000 1.0433 0.01369 0.00688 -0.0909 0.3225 1.0000
4.250 1.0593 0.01383 0.00702 -0.0887 0.3204 1.0000
4.500 1.0746 0.01396 0.00715 -0.0864 0.3179 1.0000
4.750 1.0913 0.01415 0.00731 -0.0844 0.3158 1.0000
5.000 1.1099 0.01440 0.00754 -0.0828 0.3138 1.0000
5.250 1.1319 0.01475 0.00784 -0.0820 0.3114 1.0000
5.500 1.1478 0.01486 0.00800 -0.0799 0.3100 1.0000
5.750 1.1643 0.01500 0.00818 -0.0779 0.3082 1.0000
6.000 1.1785 0.01510 0.00832 -0.0755 0.3049 1.0000
6.250 1.1937 0.01525 0.00847 -0.0733 0.3017 1.0000
6.500 1.2104 0.01548 0.00869 -0.0715 0.2990 1.0000
6.750 1.2300 0.01585 0.00901 -0.0704 0.2957 1.0000
7.000 1.2447 0.01595 0.00920 -0.0682 0.2933 1.0000
7.250 1.2604 0.01611 0.00941 -0.0663 0.2903 1.0000
7.500 1.2754 0.01627 0.00960 -0.0643 0.2862 1.0000
7.750 1.2899 0.01657 0.00986 -0.0623 0.2820 1.0000
8.000 1.3062 0.01681 0.01015 -0.0606 0.2782 1.0000
8.250 1.3232 0.01700 0.01041 -0.0591 0.2742 1.0000
8.500 1.3383 0.01727 0.01068 -0.0573 0.2687 1.0000
8.750 1.3537 0.01759 0.01101 -0.0557 0.2629 1.0000
9.000 1.3698 0.01786 0.01131 -0.0542 0.2542 1.0000
9.250 1.3850 0.01822 0.01166 -0.0527 0.2424 1.0000
9.500 1.3952 0.01886 0.01218 -0.0505 0.2200 1.0000
9.750 1.3956 0.02010 0.01316 -0.0471 0.1830 1.0000
10.000 1.3917 0.02171 0.01456 -0.0433 0.1542 1.0000
10.250 1.3890 0.02334 0.01604 -0.0399 0.1296 1.0000
10.500 1.3785 0.02553 0.01801 -0.0359 0.0957 1.0000
10.750 1.3517 0.02899 0.02120 -0.0308 0.0488 1.0000
11.000 1.3361 0.03195 0.02411 -0.0273 0.0209 1.0000
11.250 1.3381 0.03373 0.02597 -0.0255 0.0186 1.0000
11.500 1.3420 0.03544 0.02777 -0.0241 0.0175 1.0000
11.750 1.3452 0.03729 0.02972 -0.0229 0.0168 1.0000
12.000 1.3486 0.03922 0.03175 -0.0219 0.0165 1.0000
12.250 1.3494 0.04148 0.03413 -0.0209 0.0160 1.0000
12.500 1.3483 0.04404 0.03681 -0.0200 0.0155 1.0000
12.750 1.3438 0.04708 0.03997 -0.0193 0.0150 1.0000
13.000 1.3382 0.05037 0.04339 -0.0188 0.0148 1.0000
13.250 1.3291 0.05414 0.04729 -0.0184 0.0145 1.0000
13.500 1.3190 0.05816 0.05144 -0.0183 0.0144 1.0000
13.750 1.3033 0.06306 0.05649 -0.0184 0.0141 1.0000
14.000 1.2888 0.06802 0.06159 -0.0188 0.0140 1.0000
14.250 1.2738 0.07327 0.06698 -0.0196 0.0137 1.0000
14.500 1.2612 0.07838 0.07221 -0.0204 0.0137 1.0000
14.750 1.2427 0.08443 0.07840 -0.0216 0.0138 1.0000
15.000 1.2368 0.08863 0.08269 -0.0224 0.0134 1.0000
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Polar data table (+)
Polar graphs
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