MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 500,000 Max Cl/Cd: 74.35 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh93-il-500000.txt Download as CSV file: xf-mh93-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6561 0.09908 0.09684 0.0011 1.0000 0.0189
-13.750 -0.9791 0.05603 0.05186 -0.0232 1.0000 0.0126
-13.500 -0.9886 0.05299 0.04864 -0.0232 1.0000 0.0126
-13.250 -0.9928 0.05068 0.04621 -0.0227 1.0000 0.0125
-13.000 -0.9980 0.04697 0.04234 -0.0219 1.0000 0.0124
-12.750 -1.0074 0.04381 0.03897 -0.0205 1.0000 0.0124
-12.500 -1.0105 0.04115 0.03613 -0.0190 1.0000 0.0124
-12.250 -1.0099 0.03874 0.03356 -0.0173 1.0000 0.0124
-12.000 -1.0065 0.03652 0.03118 -0.0156 1.0000 0.0123
-11.750 -1.0030 0.03458 0.02905 -0.0137 1.0000 0.0124
-11.500 -0.9949 0.03287 0.02720 -0.0119 1.0000 0.0124
-11.250 -0.9860 0.03127 0.02544 -0.0101 1.0000 0.0124
-11.000 -0.9767 0.03001 0.02402 -0.0082 1.0000 0.0125
-10.750 -0.9599 0.02820 0.02210 -0.0072 1.0000 0.0126
-10.500 -0.9412 0.02637 0.02021 -0.0064 1.0000 0.0128
-10.250 -0.9246 0.02519 0.01901 -0.0053 1.0000 0.0130
-10.000 -0.9082 0.02419 0.01800 -0.0040 1.0000 0.0132
-9.750 -0.8911 0.02321 0.01698 -0.0028 1.0000 0.0134
-9.500 -0.8735 0.02231 0.01606 -0.0016 1.0000 0.0135
-9.250 -0.8517 0.02146 0.01516 -0.0012 0.9654 0.0139
-9.000 -0.8316 0.02078 0.01434 -0.0001 0.9119 0.0143
-8.750 -0.8210 0.02017 0.01359 0.0030 0.8822 0.0146
-8.000 -0.7787 0.01838 0.01145 0.0102 0.8266 0.0154
-7.750 -0.7638 0.01760 0.01062 0.0123 0.8115 0.0160
-7.500 -0.7452 0.01708 0.01004 0.0139 0.7977 0.0164
-7.250 -0.7258 0.01657 0.00945 0.0154 0.7846 0.0172
-7.000 -0.7051 0.01614 0.00891 0.0167 0.7720 0.0180
-6.750 -0.6858 0.01553 0.00827 0.0182 0.7593 0.0190
-6.500 -0.6639 0.01511 0.00780 0.0193 0.7476 0.0206
-6.250 -0.6428 0.01461 0.00723 0.0206 0.7358 0.0226
-6.000 -0.6196 0.01421 0.00679 0.0215 0.7238 0.0251
-5.750 -0.5976 0.01373 0.00627 0.0226 0.7130 0.0297
-5.500 -0.5759 0.01318 0.00576 0.0237 0.7014 0.0405
-5.250 -0.5549 0.01256 0.00528 0.0249 0.6906 0.0678
-5.000 -0.5354 0.01185 0.00481 0.0262 0.6798 0.1208
-4.750 -0.5159 0.01108 0.00440 0.0275 0.6690 0.1928
-4.500 -0.4963 0.01041 0.00405 0.0288 0.6588 0.2707
-4.250 -0.4746 0.00989 0.00378 0.0298 0.6478 0.3346
-4.000 -0.4520 0.00948 0.00355 0.0308 0.6377 0.3878
-3.750 -0.4292 0.00911 0.00335 0.0317 0.6269 0.4399
-3.500 -0.4059 0.00878 0.00319 0.0327 0.6168 0.4907
-3.250 -0.3821 0.00851 0.00304 0.0335 0.6064 0.5369
-3.000 -0.3578 0.00826 0.00292 0.0344 0.5959 0.5795
-2.750 -0.3334 0.00807 0.00283 0.0352 0.5860 0.6209
-2.500 -0.3083 0.00789 0.00278 0.0360 0.5754 0.6613
-2.250 -0.2822 0.00782 0.00275 0.0366 0.5653 0.6916
-2.000 -0.2551 0.00778 0.00272 0.0370 0.5546 0.7141
-1.750 -0.2276 0.00778 0.00271 0.0373 0.5447 0.7334
-1.500 -0.2001 0.00780 0.00270 0.0376 0.5341 0.7503
-1.250 -0.1722 0.00783 0.00271 0.0379 0.5236 0.7660
-1.000 -0.1445 0.00790 0.00273 0.0382 0.5136 0.7793
-0.750 -0.1162 0.00794 0.00277 0.0384 0.5031 0.7904
-0.500 -0.0884 0.00802 0.00277 0.0386 0.4931 0.8014
-0.250 -0.0600 0.00809 0.00282 0.0387 0.4824 0.8098
0.000 -0.0322 0.00816 0.00283 0.0389 0.4727 0.8192
0.250 -0.0038 0.00826 0.00289 0.0390 0.4623 0.8261
0.500 0.0242 0.00834 0.00293 0.0392 0.4523 0.8344
0.750 0.0521 0.00845 0.00298 0.0393 0.4426 0.8408
1.000 0.0804 0.00854 0.00306 0.0395 0.4329 0.8473
1.250 0.1078 0.00866 0.00310 0.0396 0.4233 0.8546
1.500 0.1360 0.00874 0.00318 0.0398 0.4137 0.8598
1.750 0.1636 0.00888 0.00328 0.0400 0.4048 0.8659
2.000 0.1908 0.00899 0.00334 0.0402 0.3955 0.8730
2.250 0.2182 0.00913 0.00346 0.0406 0.3869 0.8782
2.500 0.2455 0.00927 0.00358 0.0408 0.3783 0.8842
2.750 0.2721 0.00940 0.00366 0.0411 0.3703 0.8904
3.000 0.2995 0.00950 0.00375 0.0414 0.3618 0.8945
3.250 0.3265 0.00967 0.00388 0.0416 0.3543 0.8990
3.500 0.3535 0.00977 0.00398 0.0419 0.3469 0.9041
3.750 0.3793 0.00993 0.00407 0.0422 0.3396 0.9092
4.000 0.4068 0.01002 0.00419 0.0424 0.3327 0.9128
4.250 0.4333 0.01018 0.00431 0.0428 0.3255 0.9172
4.500 0.4591 0.01032 0.00444 0.0432 0.3193 0.9223
4.750 0.4851 0.01043 0.00454 0.0435 0.3130 0.9269
5.000 0.5116 0.01063 0.00470 0.0438 0.3066 0.9306
5.250 0.5382 0.01075 0.00484 0.0441 0.3007 0.9352
5.500 0.5619 0.01088 0.00496 0.0448 0.2946 0.9412
5.750 0.5895 0.01111 0.00515 0.0448 0.2885 0.9448
6.000 0.6185 0.01123 0.00532 0.0445 0.2832 0.9487
6.250 0.6443 0.01139 0.00547 0.0448 0.2774 0.9537
6.500 0.6711 0.01162 0.00566 0.0448 0.2715 0.9579
6.750 0.7039 0.01177 0.00585 0.0436 0.2661 0.9601
7.000 0.7354 0.01200 0.00606 0.0426 0.2603 0.9629
7.250 0.7651 0.01225 0.00630 0.0419 0.2547 0.9665
7.500 0.7928 0.01239 0.00649 0.0417 0.2496 0.9705
7.750 0.8278 0.01267 0.00674 0.0398 0.2438 0.9719
8.000 0.8633 0.01295 0.00703 0.0379 0.2380 0.9733
8.250 0.8987 0.01316 0.00727 0.0360 0.2322 0.9749
8.500 0.9310 0.01352 0.00758 0.0345 0.2260 0.9772
8.750 0.9622 0.01372 0.00784 0.0334 0.2212 0.9801
9.000 0.9931 0.01397 0.00812 0.0323 0.2160 0.9830
9.250 1.0271 0.01440 0.00850 0.0303 0.2104 0.9846
9.500 1.0618 0.01461 0.00879 0.0285 0.2056 0.9864
9.750 1.0942 0.01492 0.00912 0.0269 0.2006 0.9887
10.000 1.1234 0.01541 0.00957 0.0258 0.1952 0.9919
10.250 1.1563 0.01564 0.00990 0.0242 0.1908 0.9941
10.500 1.1896 0.01600 0.01028 0.0224 0.1858 0.9964
10.750 1.2207 0.01654 0.01081 0.0206 0.1804 0.9990
11.000 1.2413 0.01680 0.01115 0.0213 0.1766 1.0000
11.250 1.2437 0.01709 0.01147 0.0252 0.1735 1.0000
11.500 1.2394 0.01741 0.01181 0.0302 0.1707 1.0000
11.750 1.2296 0.01783 0.01221 0.0359 0.1679 1.0000
12.000 1.2328 0.01827 0.01270 0.0393 0.1651 1.0000
12.250 1.2426 0.01878 0.01328 0.0413 0.1614 1.0000
12.500 1.2509 0.01952 0.01403 0.0430 0.1575 1.0000
12.750 1.2561 0.02057 0.01506 0.0447 0.1536 1.0000
13.000 1.2699 0.02126 0.01586 0.0455 0.1500 1.0000
13.250 1.2798 0.02223 0.01688 0.0464 0.1458 1.0000
13.500 1.2852 0.02358 0.01821 0.0474 0.1418 1.0000
13.750 1.2946 0.02474 0.01945 0.0480 0.1381 1.0000
14.000 1.3033 0.02602 0.02078 0.0485 0.1338 1.0000
14.250 1.3062 0.02780 0.02256 0.0489 0.1296 1.0000
14.500 1.3122 0.02941 0.02424 0.0492 0.1258 1.0000
14.750 1.3176 0.03114 0.02604 0.0494 0.1216 1.0000
15.000 1.3166 0.03348 0.02838 0.0494 0.1177 1.0000
15.250 1.3188 0.03561 0.03058 0.0493 0.1140 1.0000
15.500 1.3208 0.03783 0.03286 0.0491 0.1104 1.0000
15.750 1.3162 0.04073 0.03579 0.0486 0.1069 1.0000
16.000 1.3119 0.04368 0.03878 0.0482 0.1040 1.0000
16.250 1.3123 0.04627 0.04146 0.0476 0.1010 1.0000
16.500 1.3078 0.04947 0.04472 0.0467 0.0980 1.0000
16.750 1.2989 0.05325 0.04852 0.0456 0.0953 1.0000
17.000 1.2947 0.05657 0.05192 0.0446 0.0930 1.0000
17.250 1.2917 0.05987 0.05531 0.0434 0.0904 1.0000
17.500 1.2853 0.06365 0.05914 0.0420 0.0881 1.0000
17.750 1.2749 0.06796 0.06348 0.0404 0.0857 1.0000
18.000 1.2679 0.07192 0.06749 0.0389 0.0836 1.0000
18.250 1.2640 0.07563 0.07131 0.0373 0.0814 1.0000
18.500 1.2581 0.07961 0.07536 0.0356 0.0794 1.0000
18.750 1.2489 0.08412 0.07991 0.0336 0.0774 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 93 15.98% (mh93-il)