Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.35 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin4-il-1000000.txt Download as CSV file: xf-glennmartin4-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6898 0.05061 0.04864 -0.1000 0.9616 0.0118
-12.000 -0.6897 0.04610 0.04402 -0.1005 0.9590 0.0121
-11.750 -0.7603 0.03681 0.03406 -0.0923 0.9505 0.0120
-11.500 -0.7621 0.03304 0.02991 -0.0900 0.9486 0.0120
-11.250 -0.7241 0.03369 0.03069 -0.0915 0.9482 0.0124
-11.000 -0.7294 0.03161 0.02842 -0.0863 0.9416 0.0124
-10.750 -0.7174 0.02941 0.02597 -0.0846 0.9397 0.0125
-10.500 -0.6894 0.02901 0.02555 -0.0849 0.9389 0.0129
-10.250 -0.6649 0.02764 0.02401 -0.0849 0.9381 0.0131
-10.000 -0.6591 0.02686 0.02314 -0.0806 0.9318 0.0135
-9.750 -0.6397 0.02548 0.02158 -0.0794 0.9298 0.0137
-9.500 -0.6193 0.02407 0.01996 -0.0783 0.9285 0.0140
-9.250 -0.5888 0.02371 0.01952 -0.0788 0.9277 0.0143
-9.000 -0.5847 0.02211 0.01772 -0.0744 0.9219 0.0149
-8.750 -0.5649 0.02103 0.01652 -0.0728 0.9190 0.0150
-8.500 -0.5372 0.02045 0.01591 -0.0727 0.9175 0.0154
-8.250 -0.5075 0.01982 0.01522 -0.0730 0.9163 0.0157
-8.000 -0.4778 0.01941 0.01477 -0.0733 0.9154 0.0163
-7.750 -0.4687 0.01875 0.01402 -0.0693 0.9083 0.0165
-7.500 -0.4422 0.01811 0.01330 -0.0689 0.9057 0.0169
-7.250 -0.4112 0.01763 0.01273 -0.0693 0.9039 0.0176
-7.000 -0.3853 0.01650 0.01146 -0.0688 0.9024 0.0182
-6.750 -0.3735 0.01625 0.01122 -0.0652 0.8930 0.0190
-6.500 -0.3481 0.01546 0.01036 -0.0644 0.8893 0.0191
-6.250 -0.3277 0.01548 0.01039 -0.0626 0.8813 0.0201
-5.750 -0.2703 0.01460 0.00936 -0.0625 0.8676 0.0216
-5.500 -0.2358 0.01355 0.00820 -0.0638 0.8600 0.0226
-5.250 -0.1951 0.01294 0.00755 -0.0664 0.8473 0.0235
-5.000 -0.1472 0.01241 0.00693 -0.0707 0.8323 0.0249
-4.750 -0.1059 0.01199 0.00635 -0.0734 0.8102 0.0259
-4.500 -0.0790 0.01183 0.00603 -0.0731 0.7817 0.0263
-4.250 -0.0654 0.01146 0.00547 -0.0699 0.7477 0.0274
-4.000 -0.0596 0.01155 0.00537 -0.0650 0.6977 0.0291
-3.750 -0.0524 0.01164 0.00523 -0.0605 0.6522 0.0291
-3.500 -0.0389 0.01166 0.00508 -0.0573 0.6216 0.0299
-3.250 -0.0227 0.01169 0.00497 -0.0548 0.5976 0.0309
-3.000 -0.0019 0.01164 0.00484 -0.0532 0.5840 0.0316
-2.750 0.0184 0.01153 0.00464 -0.0516 0.5708 0.0326
-2.500 0.0396 0.01140 0.00444 -0.0501 0.5597 0.0338
-2.250 0.0609 0.01137 0.00434 -0.0487 0.5472 0.0353
-2.000 0.0850 0.01127 0.00421 -0.0479 0.5397 0.0366
-1.750 0.1077 0.01124 0.00411 -0.0468 0.5308 0.0380
-1.500 0.1321 0.01117 0.00401 -0.0461 0.5220 0.0413
-1.250 0.1554 0.01117 0.00398 -0.0452 0.5136 0.0442
-1.000 0.1809 0.01113 0.00404 -0.0448 0.5061 0.0616
-0.750 0.2043 0.01119 0.00407 -0.0439 0.4979 0.0688
-0.500 0.2293 0.01122 0.00408 -0.0434 0.4909 0.0737
-0.250 0.2528 0.01131 0.00412 -0.0426 0.4825 0.0759
0.000 0.2794 0.01128 0.00407 -0.0425 0.4739 0.0816
0.250 0.3047 0.01132 0.00407 -0.0421 0.4650 0.0850
0.500 0.3304 0.01136 0.00407 -0.0419 0.4545 0.0880
0.750 0.3554 0.01144 0.00408 -0.0415 0.4443 0.0890
1.000 0.3815 0.01149 0.00409 -0.0413 0.4346 0.0902
1.250 0.4086 0.01154 0.00412 -0.0415 0.4217 0.0981
1.500 0.4342 0.01164 0.00417 -0.0412 0.4100 0.0999
1.750 0.6755 0.01073 0.00552 -0.0917 0.3718 0.9595
2.000 0.6897 0.01118 0.00590 -0.0888 0.3645 0.9864
2.250 0.7383 0.01163 0.00625 -0.0939 0.3548 0.9926
2.500 0.7988 0.01197 0.00650 -0.1017 0.3457 0.9984
2.750 0.8373 0.01213 0.00659 -0.1045 0.3397 1.0000
3.000 0.8568 0.01230 0.00670 -0.1031 0.3343 1.0000
3.250 0.8780 0.01240 0.00679 -0.1020 0.3313 1.0000
3.500 0.8990 0.01252 0.00689 -0.1008 0.3278 1.0000
3.750 0.9193 0.01268 0.00700 -0.0996 0.3235 1.0000
4.000 0.9389 0.01288 0.00716 -0.0983 0.3189 1.0000
4.250 0.9602 0.01301 0.00728 -0.0972 0.3171 1.0000
4.500 0.9817 0.01313 0.00741 -0.0963 0.3144 1.0000
4.750 1.0025 0.01328 0.00755 -0.0952 0.3116 1.0000
5.000 1.0225 0.01346 0.00771 -0.0940 0.3092 1.0000
5.250 1.0420 0.01366 0.00790 -0.0926 0.3064 1.0000
5.500 1.0600 0.01393 0.00813 -0.0911 0.3023 1.0000
5.750 1.0819 0.01404 0.00826 -0.0903 0.3003 1.0000
6.000 1.1031 0.01418 0.00842 -0.0893 0.2970 1.0000
6.250 1.1234 0.01437 0.00863 -0.0882 0.2963 1.0000
6.500 1.1435 0.01456 0.00882 -0.0871 0.2940 1.0000
6.750 1.1629 0.01478 0.00904 -0.0859 0.2913 1.0000
7.000 1.1799 0.01510 0.00933 -0.0843 0.2864 1.0000
7.250 1.2007 0.01526 0.00952 -0.0834 0.2848 1.0000
7.500 1.2213 0.01543 0.00972 -0.0825 0.2824 1.0000
7.750 1.2411 0.01564 0.00995 -0.0814 0.2802 1.0000
8.000 1.2597 0.01591 0.01020 -0.0802 0.2753 1.0000
8.250 1.2770 0.01623 0.01051 -0.0788 0.2706 1.0000
8.500 1.2986 0.01638 0.01070 -0.0781 0.2675 1.0000
8.750 1.3173 0.01665 0.01097 -0.0769 0.2625 1.0000
9.000 1.3338 0.01700 0.01131 -0.0754 0.2579 1.0000
9.250 1.3526 0.01727 0.01161 -0.0743 0.2538 1.0000
9.500 1.3713 0.01755 0.01188 -0.0733 0.2472 1.0000
9.750 1.3871 0.01796 0.01227 -0.0717 0.2387 1.0000
10.000 1.4010 0.01845 0.01271 -0.0699 0.2276 1.0000
10.250 1.4126 0.01907 0.01325 -0.0678 0.2112 1.0000
10.500 1.4199 0.01991 0.01398 -0.0649 0.1903 1.0000
10.750 1.4131 0.02145 0.01530 -0.0600 0.1562 1.0000
11.000 1.3998 0.02340 0.01703 -0.0543 0.1212 1.0000
11.250 1.3733 0.02623 0.01960 -0.0471 0.0711 1.0000
11.500 1.3555 0.02879 0.02209 -0.0417 0.0370 1.0000
12.000 1.3529 0.03220 0.02548 -0.0360 0.0189 1.0000
12.250 1.3560 0.03373 0.02706 -0.0339 0.0174 1.0000
12.500 1.3576 0.03545 0.02886 -0.0318 0.0158 1.0000
12.750 1.3625 0.03696 0.03043 -0.0303 0.0149 1.0000
13.000 1.3639 0.03881 0.03236 -0.0287 0.0148 1.0000
13.250 1.3611 0.04112 0.03473 -0.0269 0.0136 1.0000
13.500 1.3602 0.04338 0.03708 -0.0255 0.0130 1.0000
13.750 1.3555 0.04611 0.03992 -0.0241 0.0130 1.0000
14.000 1.3580 0.04824 0.04210 -0.0234 0.0124 1.0000
14.250 1.3550 0.05099 0.04495 -0.0226 0.0120 1.0000
14.500 1.3458 0.05452 0.04861 -0.0218 0.0121 1.0000
14.750 1.3442 0.05729 0.05144 -0.0214 0.0118 1.0000
15.000 1.3365 0.06083 0.05507 -0.0211 0.0111 1.0000
15.250 1.3252 0.06487 0.05923 -0.0208 0.0112 1.0000
15.500 1.3162 0.06865 0.06309 -0.0208 0.0108 1.0000
15.750 1.3047 0.07282 0.06739 -0.0207 0.0111 1.0000
16.000 1.2741 0.07953 0.07424 -0.0209 0.0104 1.0000
16.250 1.2679 0.08318 0.07797 -0.0212 0.0105 1.0000
16.500 1.2468 0.08889 0.08382 -0.0217 0.0104 1.0000
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