NACA M6 (nacam6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M6 (nacam6-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.57 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam6-il-1000000.txt Download as CSV file: xf-nacam6-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6966 0.06558 0.06376 -0.0431 1.0000 0.0225
-11.750 -0.7729 0.04970 0.04755 -0.0550 1.0000 0.0219
-11.500 -0.8254 0.04337 0.04090 -0.0517 1.0000 0.0219
-11.250 -0.8560 0.03980 0.03705 -0.0461 1.0000 0.0221
-11.000 -0.8824 0.03702 0.03401 -0.0391 1.0000 0.0222
-10.750 -0.8820 0.03614 0.03296 -0.0351 1.0000 0.0225
-10.500 -0.8784 0.03570 0.03235 -0.0313 1.0000 0.0227
-10.250 -0.9136 0.03017 0.02633 -0.0230 1.0000 0.0230
-10.000 -0.9126 0.02818 0.02419 -0.0189 1.0000 0.0232
-9.750 -0.9065 0.02684 0.02272 -0.0154 1.0000 0.0234
-9.250 -0.8671 0.02478 0.02053 -0.0136 0.9936 0.0239
-9.000 -0.8389 0.02395 0.01965 -0.0143 0.9854 0.0242
-8.750 -0.8097 0.02288 0.01848 -0.0152 0.9763 0.0246
-8.500 -0.7750 0.02185 0.01732 -0.0173 0.9690 0.0251
-8.250 -0.7377 0.02044 0.01573 -0.0199 0.9592 0.0255
-8.000 -0.6980 0.01908 0.01417 -0.0229 0.9469 0.0259
-7.750 -0.6609 0.01797 0.01288 -0.0253 0.9291 0.0261
-7.500 -0.6324 0.01724 0.01196 -0.0256 0.9076 0.0265
-7.250 -0.6096 0.01667 0.01122 -0.0245 0.8878 0.0267
-7.000 -0.5880 0.01638 0.01079 -0.0232 0.8687 0.0270
-6.750 -0.5667 0.01620 0.01049 -0.0217 0.8507 0.0271
-6.500 -0.5423 0.01458 0.00870 -0.0213 0.8349 0.0277
-6.250 -0.5188 0.01382 0.00785 -0.0204 0.8184 0.0279
-6.000 -0.4957 0.01328 0.00723 -0.0195 0.8020 0.0282
-5.750 -0.4727 0.01281 0.00669 -0.0184 0.7866 0.0286
-5.500 -0.4496 0.01244 0.00625 -0.0174 0.7721 0.0289
-5.000 -0.4031 0.01174 0.00541 -0.0154 0.7456 0.0295
-4.750 -0.3796 0.01143 0.00505 -0.0144 0.7342 0.0300
-4.500 -0.3562 0.01115 0.00471 -0.0134 0.7233 0.0304
-4.250 -0.3325 0.01087 0.00438 -0.0124 0.7130 0.0308
-4.000 -0.3084 0.01068 0.00413 -0.0116 0.7035 0.0314
-3.750 -0.2845 0.01046 0.00387 -0.0107 0.6939 0.0318
-3.500 -0.2602 0.01026 0.00362 -0.0098 0.6853 0.0321
-3.250 -0.2360 0.01010 0.00341 -0.0089 0.6763 0.0324
-3.000 -0.2129 0.00973 0.00300 -0.0079 0.6685 0.0332
-2.750 -0.1891 0.00951 0.00273 -0.0069 0.6602 0.0340
-2.500 -0.1644 0.00933 0.00254 -0.0061 0.6528 0.0349
-2.250 -0.1398 0.00919 0.00236 -0.0053 0.6448 0.0359
-2.000 -0.1149 0.00906 0.00221 -0.0046 0.6376 0.0371
-1.750 -0.0897 0.00895 0.00207 -0.0039 0.6301 0.0381
-1.500 -0.0650 0.00883 0.00193 -0.0031 0.6231 0.0408
-1.250 -0.0399 0.00870 0.00182 -0.0025 0.6162 0.0454
-1.000 -0.0172 0.00844 0.00170 -0.0013 0.6089 0.0856
-0.750 0.0059 0.00816 0.00163 -0.0003 0.6024 0.1423
-0.500 0.0290 0.00794 0.00157 0.0007 0.5954 0.1931
-0.250 0.0508 0.00764 0.00151 0.0019 0.5889 0.2714
0.000 0.0687 0.00707 0.00142 0.0039 0.5823 0.4179
0.250 0.0535 0.00565 0.00125 0.0132 0.5770 0.7755
0.500 0.1101 0.00532 0.00129 0.0069 0.5697 0.8902
0.750 0.1889 0.00557 0.00153 -0.0044 0.5606 0.9137
1.000 0.2341 0.00585 0.00180 -0.0080 0.5526 0.9260
1.250 0.2614 0.00609 0.00201 -0.0076 0.5449 0.9372
1.500 0.2997 0.00644 0.00233 -0.0095 0.5363 0.9417
1.750 0.3239 0.00670 0.00252 -0.0085 0.5262 0.9501
2.000 0.3673 0.00701 0.00279 -0.0116 0.5141 0.9520
2.250 0.4037 0.00719 0.00293 -0.0134 0.5057 0.9536
2.500 0.4406 0.00743 0.00312 -0.0152 0.4967 0.9566
2.750 0.4622 0.00759 0.00327 -0.0138 0.4890 0.9623
3.000 0.4971 0.00771 0.00334 -0.0153 0.4789 0.9630
3.250 0.5297 0.00777 0.00338 -0.0164 0.4694 0.9638
3.500 0.5613 0.00786 0.00343 -0.0173 0.4579 0.9647
3.750 0.5924 0.00797 0.00349 -0.0180 0.4457 0.9657
4.000 0.6231 0.00806 0.00356 -0.0187 0.4351 0.9671
4.250 0.6520 0.00817 0.00364 -0.0190 0.4229 0.9689
4.500 0.6699 0.00838 0.00381 -0.0169 0.4108 0.9737
4.750 0.7023 0.00848 0.00386 -0.0181 0.3956 0.9743
5.000 0.7341 0.00861 0.00393 -0.0191 0.3778 0.9750
5.250 0.7650 0.00876 0.00402 -0.0199 0.3583 0.9758
5.500 0.7949 0.00896 0.00413 -0.0206 0.3371 0.9769
5.750 0.8241 0.00917 0.00426 -0.0211 0.3161 0.9782
6.000 0.8523 0.00941 0.00442 -0.0214 0.2937 0.9801
6.250 0.8718 0.00984 0.00474 -0.0199 0.2688 0.9844
6.500 0.9020 0.01013 0.00490 -0.0208 0.2373 0.9850
6.750 0.9311 0.01051 0.00511 -0.0216 0.2045 0.9860
7.000 0.9596 0.01091 0.00537 -0.0222 0.1759 0.9871
7.250 0.9869 0.01137 0.00568 -0.0226 0.1446 0.9887
7.500 1.0106 0.01215 0.00616 -0.0225 0.0962 0.9910
7.750 1.0347 0.01276 0.00665 -0.0223 0.0753 0.9937
8.000 1.0633 0.01317 0.00699 -0.0231 0.0593 0.9949
8.250 1.0917 0.01363 0.00735 -0.0238 0.0464 0.9963
8.500 1.1202 0.01402 0.00770 -0.0245 0.0404 0.9978
8.750 1.1494 0.01435 0.00805 -0.0253 0.0371 0.9993
9.000 1.1730 0.01479 0.00847 -0.0250 0.0339 1.0000
9.250 1.1886 0.01518 0.00889 -0.0229 0.0322 1.0000
9.500 1.2051 0.01552 0.00926 -0.0210 0.0308 1.0000
9.750 1.2201 0.01595 0.00971 -0.0189 0.0294 1.0000
10.000 1.2315 0.01657 0.01034 -0.0162 0.0276 1.0000
10.250 1.2470 0.01693 0.01074 -0.0142 0.0266 1.0000
10.500 1.2611 0.01734 0.01119 -0.0120 0.0256 1.0000
10.750 1.2737 0.01781 0.01169 -0.0095 0.0247 1.0000
11.000 1.2820 0.01842 0.01232 -0.0064 0.0236 1.0000
11.250 1.2796 0.01915 0.01311 -0.0013 0.0228 1.0000
11.500 1.2841 0.01953 0.01354 0.0026 0.0224 1.0000
11.750 1.2879 0.02007 0.01413 0.0063 0.0219 1.0000
12.000 1.2931 0.02071 0.01482 0.0095 0.0212 1.0000
12.250 1.2994 0.02142 0.01556 0.0122 0.0205 1.0000
12.500 1.3038 0.02233 0.01652 0.0149 0.0199 1.0000
12.750 1.3044 0.02359 0.01782 0.0177 0.0193 1.0000
13.000 1.3023 0.02518 0.01949 0.0203 0.0188 1.0000
13.250 1.3122 0.02610 0.02047 0.0217 0.0183 1.0000
13.500 1.3168 0.02748 0.02191 0.0234 0.0180 1.0000
13.750 1.3240 0.02875 0.02323 0.0246 0.0174 1.0000
14.000 1.3282 0.03033 0.02488 0.0258 0.0171 1.0000
14.250 1.3342 0.03182 0.02642 0.0268 0.0166 1.0000
14.500 1.3367 0.03370 0.02835 0.0278 0.0162 1.0000
14.750 1.3347 0.03607 0.03079 0.0287 0.0160 1.0000
15.000 1.3273 0.03907 0.03387 0.0294 0.0154 1.0000
15.250 1.3281 0.04134 0.03622 0.0299 0.0153 1.0000
15.500 1.3289 0.04365 0.03862 0.0303 0.0151 1.0000
15.750 1.3294 0.04605 0.04111 0.0306 0.0149 1.0000
16.000 1.3320 0.04830 0.04342 0.0308 0.0146 1.0000
16.250 1.3306 0.05105 0.04625 0.0308 0.0144 1.0000
16.500 1.3319 0.05358 0.04884 0.0307 0.0140 1.0000
16.750 1.3288 0.05670 0.05204 0.0304 0.0138 1.0000
17.000 1.3251 0.05998 0.05539 0.0300 0.0136 1.0000
17.250 1.3229 0.06315 0.05863 0.0295 0.0134 1.0000
17.500 1.3152 0.06710 0.06266 0.0287 0.0132 1.0000
17.750 1.3097 0.07086 0.06649 0.0278 0.0130 1.0000
18.000 1.2942 0.07600 0.07172 0.0265 0.0127 1.0000
18.250 1.2904 0.07967 0.07547 0.0255 0.0128 1.0000
18.500 1.2743 0.08510 0.08100 0.0239 0.0125 1.0000
18.750 1.2685 0.08919 0.08518 0.0227 0.0124 1.0000
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