NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M9 AIRFOIL (m9-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.65 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m9-il-1000000-n5.txt Download as CSV file: xf-m9-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4286 0.08130 0.07850 -0.0156 0.6443 0.0089
-9.750 -0.4561 0.07483 0.07201 -0.0190 0.6403 0.0090
-9.500 -0.4625 0.06895 0.06607 -0.0242 0.6347 0.0091
-9.250 -0.4645 0.06231 0.05936 -0.0309 0.6309 0.0092
-9.000 -0.4633 0.05380 0.05072 -0.0399 0.6255 0.0095
-8.750 -0.4644 0.03631 0.03272 -0.0581 0.6226 0.0096
-8.500 -0.4534 0.02485 0.02061 -0.0660 0.6172 0.0098
-8.250 -0.4301 0.02164 0.01712 -0.0675 0.6090 0.0101
-8.000 -0.4051 0.01967 0.01493 -0.0681 0.5992 0.0105
-7.750 -0.3794 0.01813 0.01318 -0.0684 0.5878 0.0109
-7.500 -0.3531 0.01697 0.01184 -0.0685 0.5755 0.0112
-7.250 -0.3266 0.01599 0.01067 -0.0684 0.5628 0.0116
-7.000 -0.2999 0.01501 0.00953 -0.0683 0.5503 0.0122
-6.750 -0.2730 0.01418 0.00857 -0.0681 0.5397 0.0130
-6.500 -0.2458 0.01355 0.00782 -0.0679 0.5295 0.0139
-6.250 -0.2183 0.01305 0.00720 -0.0676 0.5195 0.0147
-6.000 -0.1908 0.01252 0.00657 -0.0673 0.5103 0.0159
-5.750 -0.1631 0.01210 0.00607 -0.0670 0.5004 0.0173
-5.500 -0.1352 0.01177 0.00565 -0.0667 0.4921 0.0186
-5.250 -0.1074 0.01145 0.00527 -0.0664 0.4835 0.0205
-5.000 -0.0793 0.01121 0.00496 -0.0660 0.4768 0.0222
-4.750 -0.0512 0.01097 0.00467 -0.0657 0.4700 0.0241
-4.250 0.0053 0.01064 0.00422 -0.0650 0.4580 0.0273
-4.000 0.0335 0.01043 0.00397 -0.0647 0.4522 0.0291
-3.750 0.0617 0.01030 0.00379 -0.0644 0.4458 0.0309
-3.500 0.0900 0.01017 0.00362 -0.0641 0.4394 0.0324
-3.250 0.1183 0.01005 0.00343 -0.0638 0.4324 0.0338
-3.000 0.1466 0.00992 0.00327 -0.0635 0.4260 0.0358
-2.750 0.1749 0.00982 0.00313 -0.0632 0.4190 0.0378
-2.500 0.2032 0.00976 0.00301 -0.0629 0.4130 0.0393
-2.250 0.2316 0.00963 0.00285 -0.0626 0.4094 0.0415
-2.000 0.2599 0.00952 0.00273 -0.0623 0.4051 0.0438
-1.750 0.2883 0.00945 0.00263 -0.0620 0.3998 0.0462
-1.500 0.3166 0.00942 0.00254 -0.0617 0.3949 0.0477
-1.250 0.3450 0.00931 0.00243 -0.0615 0.3918 0.0510
-1.000 0.3733 0.00924 0.00235 -0.0612 0.3883 0.0544
-0.750 0.4016 0.00920 0.00229 -0.0609 0.3839 0.0573
-0.250 0.4580 0.00911 0.00218 -0.0604 0.3739 0.0678
0.000 0.4862 0.00907 0.00214 -0.0601 0.3684 0.0741
0.250 0.5143 0.00906 0.00212 -0.0599 0.3636 0.0803
0.500 0.5424 0.00903 0.00210 -0.0596 0.3600 0.0863
0.750 0.5705 0.00901 0.00208 -0.0594 0.3562 0.0927
1.000 0.5986 0.00903 0.00208 -0.0591 0.3509 0.0962
1.250 0.6264 0.00903 0.00207 -0.0588 0.3451 0.1031
1.500 0.6544 0.00903 0.00206 -0.0586 0.3407 0.1079
1.750 0.6822 0.00905 0.00207 -0.0583 0.3338 0.1137
2.000 0.7097 0.00907 0.00207 -0.0581 0.3270 0.1231
2.250 0.7367 0.00900 0.00212 -0.0577 0.3195 0.1721
2.500 0.7656 0.00935 0.00249 -0.0577 0.3113 0.2096
2.750 0.7936 0.00950 0.00259 -0.0575 0.3021 0.2160
3.000 0.8212 0.00969 0.00272 -0.0573 0.2907 0.2188
3.250 0.8487 0.01000 0.00296 -0.0571 0.2736 0.2205
3.500 0.8752 0.01037 0.00320 -0.0568 0.2494 0.2221
3.750 0.9017 0.01067 0.00340 -0.0565 0.2321 0.2233
4.000 0.9284 0.01090 0.00357 -0.0563 0.2218 0.2243
4.250 0.9554 0.01107 0.00372 -0.0560 0.2154 0.2254
4.500 0.9821 0.01128 0.00388 -0.0557 0.2085 0.2266
4.750 1.0087 0.01149 0.00406 -0.0555 0.2021 0.2275
5.000 1.0356 0.01163 0.00419 -0.0553 0.1981 0.2278
5.250 1.0621 0.01177 0.00433 -0.0550 0.1938 0.2284
5.500 1.0884 0.01199 0.00454 -0.0547 0.1886 0.2291
5.750 1.1150 0.01213 0.00470 -0.0545 0.1858 0.2295
6.000 1.1416 0.01225 0.00484 -0.0542 0.1839 0.2298
6.250 1.1681 0.01240 0.00501 -0.0540 0.1815 0.2303
6.500 1.1944 0.01259 0.00522 -0.0537 0.1790 0.2314
6.750 1.2203 0.01277 0.00541 -0.0535 0.1763 0.2319
7.000 1.2460 0.01296 0.00561 -0.0532 0.1735 0.2321
7.250 1.2717 0.01313 0.00581 -0.0528 0.1710 0.2322
7.500 1.2975 0.01327 0.00598 -0.0526 0.1698 0.2324
7.750 1.3231 0.01343 0.00618 -0.0523 0.1681 0.2325
8.000 1.3485 0.01360 0.00638 -0.0519 0.1661 0.2327
8.250 1.3735 0.01380 0.00660 -0.0516 0.1638 0.2330
8.500 1.3981 0.01403 0.00685 -0.0512 0.1610 0.2332
8.750 1.4223 0.01429 0.00713 -0.0508 0.1577 0.2334
9.000 1.4465 0.01453 0.00739 -0.0504 0.1531 0.2337
9.250 1.4695 0.01486 0.00770 -0.0499 0.1461 0.2339
9.500 1.4923 0.01519 0.00803 -0.0493 0.1407 0.2342
9.750 1.5139 0.01561 0.00842 -0.0486 0.1320 0.2345
10.000 1.5343 0.01609 0.00887 -0.0479 0.1222 0.2350
10.250 1.5349 0.01798 0.01042 -0.0450 0.0754 0.2352
10.500 1.5429 0.01910 0.01148 -0.0428 0.0605 0.2355
10.750 1.5568 0.01973 0.01214 -0.0412 0.0573 0.2358
11.000 1.5632 0.02041 0.01285 -0.0384 0.0547 0.2360
11.250 1.5660 0.02139 0.01387 -0.0356 0.0514 0.2361
11.500 1.5731 0.02235 0.01488 -0.0338 0.0495 0.2362
11.750 1.5811 0.02341 0.01599 -0.0324 0.0482 0.2366
12.000 1.5868 0.02476 0.01739 -0.0312 0.0457 0.2368
12.250 1.5882 0.02661 0.01927 -0.0300 0.0423 0.2370
12.500 1.5922 0.02834 0.02104 -0.0291 0.0392 0.2370
12.750 1.5880 0.03088 0.02358 -0.0282 0.0316 0.2372
13.000 1.5685 0.03500 0.02766 -0.0274 0.0171 0.2372
13.250 1.5613 0.03815 0.03088 -0.0270 0.0136 0.2372
13.500 1.5605 0.04077 0.03357 -0.0268 0.0124 0.2373
13.750 1.5593 0.04351 0.03640 -0.0268 0.0116 0.2374
14.000 1.5550 0.04671 0.03968 -0.0269 0.0106 0.2376
14.500 1.5480 0.05321 0.04633 -0.0277 0.0094 0.2378
14.750 1.5456 0.05651 0.04972 -0.0283 0.0092 0.2379
15.000 1.5406 0.06023 0.05354 -0.0290 0.0086 0.2383
15.250 1.5359 0.06404 0.05743 -0.0300 0.0082 0.2384
15.500 1.5297 0.06811 0.06158 -0.0310 0.0079 0.2386
15.750 1.5213 0.07262 0.06619 -0.0324 0.0075 0.2386
16.000 1.5148 0.07697 0.07062 -0.0337 0.0073 0.2388
16.250 1.5094 0.08119 0.07494 -0.0351 0.0070 0.2391
16.500 1.5032 0.08566 0.07949 -0.0366 0.0069 0.2393
16.750 1.4960 0.09035 0.08429 -0.0383 0.0067 0.2394
17.000 1.4880 0.09528 0.08930 -0.0402 0.0065 0.2395
17.250 1.4791 0.10044 0.09455 -0.0422 0.0062 0.2397
17.500 1.4713 0.10549 0.09971 -0.0443 0.0061 0.2399
17.750 1.4611 0.11105 0.10536 -0.0466 0.0060 0.2401
18.000 1.4507 0.11676 0.11116 -0.0491 0.0057 0.2402
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