Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 200,000 Max Cl/Cd: 57.9 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin2-il-200000-n5.txt Download as CSV file: xf-glennmartin2-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1180 0.09102 0.08757 -0.0777 0.9531 0.0212
-10.000 -0.1103 0.08612 0.08268 -0.0820 0.9498 0.0215
-9.750 -0.1101 0.08185 0.07842 -0.0844 0.9413 0.0218
-9.500 -0.1052 0.07652 0.07310 -0.0893 0.9366 0.0220
-9.250 -0.1123 0.07073 0.06733 -0.0938 0.9277 0.0225
-8.750 -0.2622 0.03165 0.02694 -0.1075 0.8984 0.0241
-8.500 -0.2307 0.03148 0.02682 -0.1084 0.8924 0.0250
-8.250 -0.2034 0.02960 0.02469 -0.1096 0.8875 0.0264
-8.000 -0.1998 0.02703 0.02168 -0.1062 0.8773 0.0275
-7.750 -0.1784 0.02421 0.01819 -0.1059 0.8720 0.0296
-7.500 -0.1654 0.02322 0.01707 -0.1033 0.8621 0.0308
-7.250 -0.1320 0.02261 0.01638 -0.1045 0.8562 0.0325
-7.000 -0.1155 0.02170 0.01526 -0.1022 0.8457 0.0340
-6.750 -0.0906 0.02056 0.01378 -0.1016 0.8373 0.0361
-6.500 -0.0666 0.01964 0.01265 -0.1008 0.8280 0.0380
-6.250 -0.0433 0.01917 0.01211 -0.0998 0.8173 0.0397
-6.000 -0.0156 0.01863 0.01142 -0.0996 0.8071 0.0418
-5.750 0.0105 0.01798 0.01055 -0.0991 0.7948 0.0442
-5.500 0.0351 0.01728 0.00965 -0.0982 0.7805 0.0458
-5.250 0.0604 0.01682 0.00913 -0.0975 0.7655 0.0479
-5.000 0.0871 0.01651 0.00870 -0.0970 0.7489 0.0505
-4.750 0.1139 0.01608 0.00809 -0.0966 0.7301 0.0530
-4.500 0.1402 0.01566 0.00746 -0.0959 0.7104 0.0552
-4.250 0.1654 0.01534 0.00704 -0.0952 0.6908 0.0581
-4.000 0.1902 0.01521 0.00675 -0.0944 0.6726 0.0621
-3.750 0.2142 0.01507 0.00639 -0.0934 0.6560 0.0663
-3.500 0.2367 0.01483 0.00608 -0.0921 0.6418 0.0707
-3.250 0.2596 0.01473 0.00586 -0.0910 0.6288 0.0761
-3.000 0.2824 0.01467 0.00564 -0.0898 0.6158 0.0811
-2.750 0.3039 0.01451 0.00543 -0.0884 0.6034 0.0876
-2.500 0.3254 0.01446 0.00528 -0.0870 0.5898 0.0937
-2.250 0.3460 0.01436 0.00512 -0.0854 0.5749 0.0992
-2.000 0.3654 0.01427 0.00498 -0.0836 0.5570 0.1060
-1.750 0.3841 0.01424 0.00486 -0.0816 0.5320 0.1133
-1.500 0.3981 0.01423 0.00475 -0.0788 0.4932 0.1236
-1.250 0.4086 0.01436 0.00469 -0.0752 0.4565 0.1346
-0.750 0.4350 0.01462 0.00485 -0.0693 0.4181 0.1892
-0.500 0.4513 0.01477 0.00495 -0.0670 0.4066 0.2181
-0.250 0.4684 0.01496 0.00505 -0.0648 0.3977 0.2377
0.000 0.4871 0.01510 0.00513 -0.0630 0.3902 0.2524
0.250 0.5048 0.01527 0.00522 -0.0610 0.3840 0.2632
0.500 0.5251 0.01538 0.00530 -0.0595 0.3789 0.2738
0.750 0.5451 0.01553 0.00539 -0.0580 0.3738 0.2851
1.000 0.5643 0.01566 0.00548 -0.0564 0.3695 0.2933
1.250 0.5842 0.01581 0.00558 -0.0549 0.3660 0.3034
1.750 0.6250 0.01599 0.00579 -0.0522 0.3590 0.3278
2.000 0.6450 0.01609 0.00592 -0.0508 0.3558 0.3448
2.250 0.6637 0.01605 0.00607 -0.0492 0.3530 0.4123
3.250 0.9488 0.01715 0.00805 -0.0885 0.3370 1.0000
3.500 0.9677 0.01742 0.00826 -0.0870 0.3351 1.0000
3.750 0.9879 0.01771 0.00848 -0.0857 0.3333 1.0000
4.000 1.0064 0.01791 0.00870 -0.0841 0.3315 1.0000
4.250 1.0255 0.01813 0.00893 -0.0826 0.3298 1.0000
4.500 1.0446 0.01837 0.00919 -0.0812 0.3279 1.0000
4.750 1.0639 0.01862 0.00944 -0.0798 0.3262 1.0000
5.000 1.0821 0.01887 0.00969 -0.0782 0.3239 1.0000
5.250 1.1002 0.01913 0.00994 -0.0766 0.3217 1.0000
5.500 1.1188 0.01943 0.01021 -0.0752 0.3191 1.0000
5.750 1.1403 0.01978 0.01051 -0.0744 0.3168 1.0000
6.000 1.1555 0.02001 0.01082 -0.0723 0.3143 1.0000
6.250 1.1721 0.02026 0.01114 -0.0705 0.3118 1.0000
6.500 1.1884 0.02053 0.01145 -0.0687 0.3089 1.0000
6.750 1.2054 0.02082 0.01177 -0.0671 0.3064 1.0000
7.000 1.2229 0.02114 0.01210 -0.0656 0.3040 1.0000
7.250 1.2420 0.02149 0.01245 -0.0645 0.3017 1.0000
7.500 1.2588 0.02183 0.01284 -0.0629 0.2992 1.0000
7.750 1.2694 0.02211 0.01323 -0.0603 0.2948 1.0000
8.000 1.2799 0.02241 0.01359 -0.0577 0.2898 1.0000
8.250 1.2900 0.02280 0.01393 -0.0552 0.2844 1.0000
8.500 1.3016 0.02316 0.01444 -0.0530 0.2791 1.0000
8.750 1.3135 0.02357 0.01491 -0.0509 0.2742 1.0000
9.000 1.3241 0.02407 0.01539 -0.0487 0.2694 1.0000
9.250 1.3370 0.02451 0.01598 -0.0469 0.2628 1.0000
9.500 1.3468 0.02508 0.01658 -0.0448 0.2565 1.0000
9.750 1.3560 0.02570 0.01729 -0.0428 0.2450 1.0000
10.000 1.3642 0.02645 0.01805 -0.0407 0.2312 1.0000
10.250 1.3685 0.02748 0.01902 -0.0383 0.2110 1.0000
10.500 1.3662 0.02902 0.02041 -0.0355 0.1852 1.0000
10.750 1.3613 0.03093 0.02218 -0.0326 0.1645 1.0000
11.000 1.3529 0.03327 0.02440 -0.0298 0.1448 1.0000
11.250 1.3455 0.03569 0.02675 -0.0273 0.1243 1.0000
11.500 1.3289 0.03904 0.02996 -0.0247 0.0968 1.0000
11.750 1.3068 0.04318 0.03397 -0.0224 0.0661 1.0000
12.000 1.2849 0.04771 0.03846 -0.0208 0.0418 1.0000
12.250 1.2642 0.05248 0.04325 -0.0198 0.0234 1.0000
12.500 1.2546 0.05628 0.04717 -0.0194 0.0202 1.0000
12.750 1.2472 0.05997 0.05098 -0.0192 0.0190 1.0000
13.000 1.2395 0.06381 0.05495 -0.0192 0.0181 1.0000
13.250 1.2313 0.06786 0.05915 -0.0194 0.0174 1.0000
13.500 1.2232 0.07205 0.06349 -0.0198 0.0168 1.0000
13.750 1.2157 0.07627 0.06785 -0.0204 0.0167 1.0000
14.000 1.2045 0.08115 0.07289 -0.0212 0.0159 1.0000
14.250 1.1945 0.08594 0.07783 -0.0222 0.0155 1.0000
14.500 1.1868 0.09046 0.08249 -0.0231 0.0156 1.0000
14.750 1.1757 0.09549 0.08766 -0.0242 0.0150 1.0000
15.000 1.1654 0.10046 0.09277 -0.0253 0.0148 1.0000
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Polar data table (+)
Polar graphs
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