MH 23 8% (mh23-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 200,000 Max Cl/Cd: 66.86 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh23-il-200000.txt Download as CSV file: xf-mh23-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4851 0.08844 0.08499 -0.0282 1.0000 0.0352
-8.500 -0.4870 0.08494 0.08153 -0.0297 1.0000 0.0359
-8.250 -0.4928 0.08120 0.07784 -0.0315 1.0000 0.0367
-8.000 -0.5046 0.07774 0.07445 -0.0330 1.0000 0.0369
-7.750 -0.5207 0.07498 0.07173 -0.0318 1.0000 0.0370
-7.500 -0.5326 0.07192 0.06867 -0.0308 1.0000 0.0374
-7.250 -0.5434 0.06878 0.06550 -0.0295 1.0000 0.0381
-7.000 -0.5508 0.06568 0.06234 -0.0280 1.0000 0.0389
-6.750 -0.5560 0.06237 0.05892 -0.0265 1.0000 0.0403
-6.500 -0.5586 0.06061 0.05673 -0.0243 1.0000 0.0426
-6.250 -0.5584 0.05867 0.05451 -0.0214 1.0000 0.0429
-6.000 -0.5641 0.05141 0.04729 -0.0199 1.0000 0.0443
-5.750 -0.5576 0.04844 0.04436 -0.0180 1.0000 0.0457
-5.500 -0.5501 0.04593 0.04177 -0.0160 1.0000 0.0478
-5.250 -0.5412 0.04338 0.03904 -0.0139 1.0000 0.0509
-5.000 -0.5346 0.04061 0.03563 -0.0107 1.0000 0.0572
-4.750 -0.5222 0.03754 0.03265 -0.0093 1.0000 0.0595
-4.500 -0.5085 0.03550 0.03046 -0.0074 1.0000 0.0643
-4.250 -0.4786 0.02067 0.01575 -0.0066 1.0000 0.0728
-4.000 -0.4654 0.01876 0.01351 -0.0046 1.0000 0.0840
-3.750 -0.4519 0.02568 0.01921 0.0006 1.0000 0.0394
-3.500 -0.4267 0.02231 0.01526 0.0031 1.0000 0.0266
-3.250 -0.4022 0.01988 0.01235 0.0050 1.0000 0.0227
-3.000 -0.3784 0.01870 0.01089 0.0066 1.0000 0.0208
-2.750 -0.3561 0.01787 0.00995 0.0079 1.0000 0.0202
-2.500 -0.3343 0.01682 0.00876 0.0093 1.0000 0.0199
-2.250 -0.3139 0.01570 0.00759 0.0109 1.0000 0.0201
-2.000 -0.2922 0.01470 0.00650 0.0121 0.9995 0.0214
-1.750 -0.1208 0.01133 0.00660 -0.0151 1.0000 1.0000
-1.500 -0.1095 0.01133 0.00647 -0.0123 1.0000 1.0000
-1.250 -0.0974 0.01137 0.00638 -0.0098 1.0000 1.0000
-1.000 -0.0835 0.01144 0.00630 -0.0075 0.9998 1.0000
-0.750 -0.0365 0.01166 0.00638 -0.0120 0.9946 1.0000
-0.500 0.0073 0.01179 0.00640 -0.0158 0.9884 1.0000
-0.250 0.0554 0.01199 0.00648 -0.0204 0.9829 1.0000
0.000 0.0986 0.01207 0.00650 -0.0239 0.9757 1.0000
0.250 0.1484 0.01217 0.00655 -0.0287 0.9702 1.0000
0.500 0.1906 0.01215 0.00653 -0.0319 0.9620 1.0000
0.750 0.2442 0.01211 0.00650 -0.0373 0.9568 1.0000
1.000 0.2871 0.01200 0.00641 -0.0404 0.9480 1.0000
1.250 0.3453 0.01178 0.00625 -0.0466 0.9435 1.0000
1.500 0.3902 0.01152 0.00604 -0.0499 0.9341 1.0000
1.750 0.4345 0.01118 0.00580 -0.0529 0.9248 1.0000
2.000 0.4717 0.01079 0.00549 -0.0543 0.9128 1.0000
2.250 0.4988 0.01044 0.00521 -0.0534 0.8968 1.0000
2.500 0.5231 0.01007 0.00490 -0.0519 0.8784 1.0000
2.750 0.5427 0.00977 0.00473 -0.0495 0.8537 1.0000
3.000 0.5650 0.00946 0.00446 -0.0475 0.8231 1.0000
3.250 0.5891 0.00918 0.00413 -0.0458 0.7776 1.0000
3.500 0.6124 0.00916 0.00390 -0.0440 0.7122 1.0000
3.750 0.6317 0.00949 0.00391 -0.0417 0.6358 1.0000
4.000 0.6489 0.01000 0.00409 -0.0393 0.5574 1.0000
4.250 0.6652 0.01059 0.00441 -0.0370 0.4800 1.0000
4.500 0.6811 0.01124 0.00474 -0.0348 0.4037 1.0000
4.750 0.6972 0.01191 0.00512 -0.0327 0.3320 1.0000
5.000 0.7131 0.01266 0.00555 -0.0307 0.2607 1.0000
5.250 0.7291 0.01346 0.00604 -0.0288 0.1928 1.0000
5.500 0.7449 0.01437 0.00662 -0.0269 0.1303 1.0000
5.750 0.7598 0.01544 0.00745 -0.0247 0.0848 1.0000
6.000 0.7737 0.01669 0.00859 -0.0220 0.0595 1.0000
6.250 0.7877 0.01802 0.00994 -0.0194 0.0485 1.0000
6.500 0.8020 0.01946 0.01137 -0.0170 0.0390 1.0000
6.750 0.8210 0.02004 0.01218 -0.0154 0.0298 1.0000
7.000 0.8362 0.02114 0.01333 -0.0134 0.0183 1.0000
7.250 0.8505 0.02361 0.01602 -0.0106 0.0152 1.0000
7.500 0.8678 0.02580 0.01849 -0.0084 0.0138 1.0000
7.750 0.8833 0.02840 0.02144 -0.0059 0.0129 1.0000
8.000 0.8952 0.03141 0.02487 -0.0030 0.0127 1.0000
8.250 0.9024 0.03477 0.02870 0.0004 0.0129 1.0000
8.500 0.9044 0.03841 0.03280 0.0042 0.0132 1.0000
8.750 0.9017 0.04228 0.03710 0.0082 0.0137 1.0000
9.000 0.8953 0.04605 0.04123 0.0121 0.0142 1.0000
9.250 0.8842 0.04985 0.04534 0.0160 0.0146 1.0000
9.500 0.8697 0.05321 0.04892 0.0198 0.0149 1.0000
9.750 0.8512 0.05634 0.05223 0.0235 0.0152 1.0000
10.000 0.8325 0.05978 0.05583 0.0258 0.0154 1.0000
10.250 0.8127 0.06382 0.06002 0.0264 0.0156 1.0000
10.500 0.7953 0.06824 0.06457 0.0251 0.0157 1.0000
10.750 0.7758 0.07426 0.07072 0.0213 0.0157 1.0000
11.000 0.7573 0.08242 0.07897 0.0149 0.0157 1.0000
11.250 0.7427 0.09214 0.08871 0.0080 0.0159 1.0000
11.500 0.7315 0.10013 0.09667 0.0038 0.0164 1.0000
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Polar data table (+)
Polar graphs
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