MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 200,000 Max Cl/Cd: 52.74 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh92-il-200000.txt Download as CSV file: xf-mh92-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6577 0.09093 0.08758 -0.0151 1.0000 0.0688
-11.250 -0.7057 0.08345 0.07994 -0.0207 1.0000 0.0689
-11.000 -0.7389 0.07888 0.07524 -0.0222 1.0000 0.0689
-10.750 -0.7928 0.04707 0.04250 -0.0229 1.0000 0.0339
-10.500 -0.8624 0.05241 0.04739 -0.0164 1.0000 0.0337
-10.250 -0.8884 0.04616 0.04043 -0.0116 1.0000 0.0292
-10.000 -0.8802 0.04309 0.03718 -0.0101 1.0000 0.0288
-9.750 -0.8727 0.04012 0.03396 -0.0082 1.0000 0.0282
-9.500 -0.8624 0.03726 0.03080 -0.0064 1.0000 0.0278
-9.250 -0.8483 0.03455 0.02777 -0.0049 1.0000 0.0273
-9.000 -0.8304 0.03228 0.02522 -0.0038 1.0000 0.0272
-8.750 -0.8094 0.03043 0.02318 -0.0031 1.0000 0.0276
-8.500 -0.7876 0.02892 0.02148 -0.0024 1.0000 0.0285
-8.250 -0.7635 0.02747 0.01987 -0.0021 1.0000 0.0290
-8.000 -0.7389 0.02603 0.01828 -0.0020 1.0000 0.0300
-7.750 -0.7131 0.02462 0.01695 -0.0023 1.0000 0.0309
-7.500 -0.6697 0.02311 0.01544 -0.0055 0.9725 0.0322
-7.250 -0.6312 0.02186 0.01412 -0.0077 0.9495 0.0336
-7.000 -0.6072 0.02073 0.01297 -0.0070 0.9249 0.0354
-6.750 -0.5925 0.02006 0.01229 -0.0044 0.9013 0.0370
-6.500 -0.5785 0.01948 0.01160 -0.0015 0.8817 0.0394
-6.250 -0.5659 0.01876 0.01089 0.0013 0.8640 0.0431
-6.000 -0.5512 0.01807 0.01017 0.0038 0.8476 0.0487
-5.750 -0.5360 0.01732 0.00940 0.0062 0.8323 0.0575
-5.500 -0.5227 0.01629 0.00849 0.0088 0.8180 0.0821
-5.250 -0.5172 0.01456 0.00755 0.0122 0.8050 0.2077
-5.000 -0.5060 0.01356 0.00709 0.0150 0.7920 0.3245
-4.750 -0.4895 0.01296 0.00679 0.0171 0.7783 0.3994
-4.500 -0.4712 0.01253 0.00657 0.0191 0.7658 0.4626
-4.250 -0.4516 0.01221 0.00637 0.0210 0.7545 0.5176
-4.000 -0.4300 0.01192 0.00625 0.0226 0.7410 0.5663
-3.750 -0.4074 0.01173 0.00616 0.0241 0.7287 0.6106
-3.500 -0.3843 0.01162 0.00611 0.0257 0.7178 0.6507
-3.250 -0.3597 0.01159 0.00617 0.0270 0.7045 0.6878
-3.000 -0.3344 0.01167 0.00625 0.0283 0.6925 0.7189
-2.750 -0.3086 0.01178 0.00628 0.0294 0.6815 0.7424
-2.500 -0.2820 0.01188 0.00634 0.0303 0.6683 0.7624
-2.250 -0.2551 0.01203 0.00642 0.0312 0.6565 0.7795
-2.000 -0.2279 0.01222 0.00650 0.0321 0.6453 0.7945
-1.750 -0.2003 0.01239 0.00663 0.0329 0.6324 0.8084
-1.500 -0.1741 0.01255 0.00669 0.0338 0.6207 0.8220
-1.250 -0.1455 0.01278 0.00679 0.0345 0.6092 0.8325
-1.000 -0.1171 0.01295 0.00690 0.0350 0.5964 0.8424
-0.750 -0.0907 0.01311 0.00696 0.0358 0.5849 0.8537
-0.500 -0.0596 0.01333 0.00706 0.0359 0.5731 0.8607
-0.250 -0.0317 0.01349 0.00716 0.0363 0.5605 0.8705
0.000 -0.0006 0.01368 0.00725 0.0362 0.5487 0.8775
0.250 0.0323 0.01390 0.00734 0.0358 0.5370 0.8842
0.500 0.0594 0.01400 0.00739 0.0363 0.5246 0.8934
0.750 0.0978 0.01424 0.00753 0.0347 0.5121 0.8980
1.000 0.1241 0.01438 0.00754 0.0353 0.5015 0.9078
1.250 0.1649 0.01456 0.00768 0.0331 0.4883 0.9121
1.500 0.2076 0.01477 0.00779 0.0305 0.4757 0.9163
1.750 0.2320 0.01489 0.00779 0.0312 0.4660 0.9260
2.000 0.2786 0.01501 0.00787 0.0276 0.4528 0.9285
2.250 0.3211 0.01515 0.00793 0.0247 0.4410 0.9321
2.500 0.3542 0.01528 0.00793 0.0237 0.4311 0.9383
2.750 0.3878 0.01534 0.00800 0.0224 0.4201 0.9439
3.000 0.4281 0.01546 0.00803 0.0199 0.4099 0.9475
3.250 0.4613 0.01555 0.00808 0.0186 0.3999 0.9533
3.500 0.4943 0.01567 0.00815 0.0174 0.3910 0.9585
3.750 0.5337 0.01575 0.00818 0.0149 0.3815 0.9623
4.000 0.5668 0.01589 0.00830 0.0136 0.3726 0.9678
4.250 0.6015 0.01598 0.00833 0.0120 0.3641 0.9723
4.500 0.6395 0.01610 0.00847 0.0096 0.3554 0.9763
4.750 0.6723 0.01624 0.00855 0.0083 0.3477 0.9815
5.000 0.7096 0.01635 0.00868 0.0060 0.3393 0.9852
5.250 0.7464 0.01644 0.00874 0.0039 0.3313 0.9894
5.500 0.7807 0.01665 0.00895 0.0021 0.3242 0.9936
5.750 0.8185 0.01672 0.00903 -0.0003 0.3162 0.9973
6.000 0.8508 0.01695 0.00920 -0.0017 0.3095 1.0000
6.250 0.8714 0.01714 0.00948 -0.0008 0.3033 1.0000
6.500 0.8919 0.01736 0.00967 0.0001 0.2977 1.0000
6.750 0.9121 0.01768 0.00999 0.0010 0.2922 1.0000
7.000 0.9318 0.01790 0.01030 0.0021 0.2861 1.0000
7.250 0.9515 0.01816 0.01053 0.0031 0.2810 1.0000
7.500 0.9705 0.01854 0.01092 0.0043 0.2758 1.0000
7.750 0.9886 0.01880 0.01129 0.0056 0.2700 1.0000
8.000 1.0069 0.01909 0.01155 0.0069 0.2651 1.0000
8.250 1.0245 0.01951 0.01198 0.0083 0.2601 1.0000
8.500 1.0405 0.01982 0.01241 0.0099 0.2546 1.0000
8.750 1.0570 0.02011 0.01269 0.0115 0.2498 1.0000
9.000 1.0734 0.02059 0.01313 0.0131 0.2452 1.0000
9.250 1.0864 0.02094 0.01363 0.0152 0.2402 1.0000
9.500 1.1005 0.02126 0.01399 0.0172 0.2355 1.0000
9.750 1.1167 0.02173 0.01435 0.0188 0.2312 1.0000
10.000 1.1265 0.02215 0.01495 0.0214 0.2268 1.0000
10.250 1.1378 0.02252 0.01539 0.0238 0.2221 1.0000
10.500 1.1517 0.02290 0.01574 0.0258 0.2179 1.0000
10.750 1.1649 0.02348 0.01635 0.0277 0.2135 1.0000
11.000 1.1746 0.02393 0.01694 0.0301 0.2087 1.0000
11.250 1.1885 0.02435 0.01737 0.0319 0.2043 1.0000
11.500 1.2049 0.02498 0.01795 0.0331 0.1997 1.0000
11.750 1.2127 0.02559 0.01874 0.0354 0.1951 1.0000
12.000 1.2243 0.02611 0.01930 0.0372 0.1904 1.0000
12.250 1.2421 0.02680 0.01988 0.0381 0.1858 1.0000
12.500 1.2405 0.02757 0.02087 0.0413 0.1820 1.0000
12.750 1.2453 0.02836 0.02174 0.0434 0.1777 1.0000
13.000 1.2572 0.02909 0.02241 0.0446 0.1733 1.0000
13.250 1.2604 0.03030 0.02374 0.0461 0.1692 1.0000
13.500 1.2621 0.03156 0.02513 0.0475 0.1649 1.0000
13.750 1.2699 0.03263 0.02620 0.0483 0.1609 1.0000
14.000 1.2769 0.03399 0.02758 0.0491 0.1566 1.0000
14.250 1.2740 0.03588 0.02965 0.0498 0.1528 1.0000
14.500 1.2779 0.03742 0.03123 0.0502 0.1488 1.0000
14.750 1.2910 0.03857 0.03228 0.0506 0.1446 1.0000
15.000 1.2815 0.04130 0.03525 0.0506 0.1414 1.0000
15.250 1.2794 0.04363 0.03769 0.0504 0.1378 1.0000
15.500 1.2847 0.04534 0.03939 0.0504 0.1342 1.0000
15.750 1.2869 0.04756 0.04165 0.0502 0.1308 1.0000
16.000 1.2759 0.05106 0.04535 0.0493 0.1279 1.0000
16.250 1.2724 0.05389 0.04827 0.0484 0.1246 1.0000
16.500 1.2804 0.05553 0.04984 0.0482 0.1213 1.0000
16.750 1.2740 0.05896 0.05339 0.0471 0.1185 1.0000
17.000 1.2584 0.06366 0.05829 0.0450 0.1160 1.0000
17.250 1.2518 0.06741 0.06214 0.0434 0.1131 1.0000
17.500 1.2596 0.06924 0.06393 0.0428 0.1100 1.0000
17.750 1.2554 0.07282 0.06758 0.0414 0.1074 1.0000
18.000 1.2308 0.07950 0.07449 0.0379 0.1054 1.0000
18.250 1.2124 0.08551 0.08066 0.0348 0.1031 1.0000
18.500 1.2157 0.08825 0.08341 0.0335 0.1003 1.0000
18.750 1.2337 0.08860 0.08366 0.0338 0.0972 1.0000
19.000 1.1931 0.09852 0.09387 0.0282 0.0958 1.0000
19.250 1.1120 0.11620 0.11191 0.0182 0.0949 1.0000
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Polar data table (+)
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