NACA M6 (nacam6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M6 (nacam6-il) Reynolds number: 1,000,000 Max Cl/Cd: 81 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam6-il-1000000-n5.txt Download as CSV file: xf-nacam6-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0670 0.05371 0.05117 -0.0565 1.0000 0.0176
-15.500 -1.1037 0.04543 0.04263 -0.0617 1.0000 0.0176
-15.250 -1.1172 0.04165 0.03869 -0.0621 1.0000 0.0177
-15.000 -1.1232 0.03905 0.03595 -0.0614 1.0000 0.0179
-14.750 -1.1266 0.03690 0.03366 -0.0600 1.0000 0.0180
-14.500 -1.1273 0.03514 0.03177 -0.0583 1.0000 0.0181
-14.250 -1.1288 0.03342 0.02992 -0.0560 1.0000 0.0182
-14.000 -1.1267 0.03203 0.02840 -0.0536 1.0000 0.0183
-13.750 -1.1229 0.03082 0.02707 -0.0510 1.0000 0.0183
-13.500 -1.1195 0.02961 0.02575 -0.0482 1.0000 0.0185
-13.250 -1.1190 0.02824 0.02425 -0.0449 1.0000 0.0187
-13.000 -1.1130 0.02726 0.02319 -0.0419 1.0000 0.0189
-12.750 -1.1053 0.02645 0.02230 -0.0390 1.0000 0.0190
-12.500 -1.0954 0.02585 0.02166 -0.0362 1.0000 0.0191
-12.250 -1.0866 0.02519 0.02093 -0.0331 1.0000 0.0192
-12.000 -1.0763 0.02465 0.02034 -0.0302 1.0000 0.0193
-11.750 -1.0626 0.02421 0.01986 -0.0279 1.0000 0.0195
-11.500 -1.0487 0.02366 0.01924 -0.0256 1.0000 0.0196
-11.250 -1.0350 0.02305 0.01857 -0.0232 1.0000 0.0198
-11.000 -1.0203 0.02252 0.01798 -0.0210 1.0000 0.0199
-10.750 -1.0067 0.02184 0.01721 -0.0185 1.0000 0.0201
-10.500 -0.9873 0.02116 0.01646 -0.0173 0.9890 0.0203
-10.250 -0.9560 0.02030 0.01549 -0.0186 0.9750 0.0205
-10.000 -0.9146 0.01945 0.01455 -0.0221 0.9636 0.0208
-9.750 -0.8692 0.01857 0.01355 -0.0265 0.9508 0.0211
-9.500 -0.8239 0.01772 0.01258 -0.0308 0.9327 0.0214
-9.250 -0.7905 0.01709 0.01178 -0.0323 0.9068 0.0216
-9.000 -0.7685 0.01659 0.01113 -0.0313 0.8828 0.0218
-8.750 -0.7484 0.01618 0.01059 -0.0298 0.8629 0.0219
-8.500 -0.7281 0.01583 0.01011 -0.0283 0.8443 0.0221
-8.250 -0.7079 0.01541 0.00957 -0.0268 0.8256 0.0222
-8.000 -0.6870 0.01510 0.00915 -0.0254 0.8075 0.0223
-7.750 -0.6657 0.01481 0.00876 -0.0241 0.7902 0.0224
-7.500 -0.6440 0.01452 0.00837 -0.0228 0.7736 0.0225
-7.250 -0.6241 0.01378 0.00752 -0.0213 0.7589 0.0230
-7.000 -0.6027 0.01334 0.00699 -0.0201 0.7459 0.0232
-6.750 -0.5806 0.01299 0.00658 -0.0189 0.7334 0.0234
-6.500 -0.5578 0.01269 0.00622 -0.0178 0.7219 0.0236
-6.250 -0.5349 0.01241 0.00587 -0.0168 0.7113 0.0238
-6.000 -0.5117 0.01214 0.00554 -0.0158 0.7012 0.0240
-5.750 -0.4881 0.01188 0.00523 -0.0149 0.6919 0.0242
-5.500 -0.4646 0.01164 0.00493 -0.0140 0.6824 0.0245
-5.250 -0.4406 0.01141 0.00466 -0.0131 0.6741 0.0247
-4.750 -0.3925 0.01097 0.00413 -0.0114 0.6574 0.0252
-4.500 -0.3684 0.01078 0.00389 -0.0106 0.6493 0.0255
-4.250 -0.3438 0.01058 0.00366 -0.0098 0.6418 0.0257
-4.000 -0.3194 0.01040 0.00344 -0.0090 0.6342 0.0260
-3.750 -0.2947 0.01023 0.00323 -0.0083 0.6270 0.0262
-3.500 -0.2699 0.01007 0.00304 -0.0076 0.6198 0.0266
-3.250 -0.2449 0.00995 0.00289 -0.0069 0.6131 0.0270
-3.000 -0.2197 0.00983 0.00274 -0.0062 0.6057 0.0272
-2.750 -0.1950 0.00970 0.00258 -0.0055 0.5990 0.0276
-2.500 -0.1701 0.00952 0.00238 -0.0048 0.5918 0.0282
-2.250 -0.1453 0.00940 0.00222 -0.0041 0.5846 0.0288
-2.000 -0.1200 0.00928 0.00210 -0.0034 0.5784 0.0294
-1.750 -0.0948 0.00918 0.00198 -0.0028 0.5714 0.0301
-1.500 -0.0696 0.00910 0.00188 -0.0021 0.5650 0.0308
-1.250 -0.0441 0.00901 0.00179 -0.0015 0.5582 0.0318
-1.000 -0.0188 0.00896 0.00171 -0.0009 0.5517 0.0327
-0.750 0.0068 0.00889 0.00163 -0.0004 0.5452 0.0342
-0.500 0.0320 0.00881 0.00156 0.0003 0.5380 0.0382
-0.250 0.0559 0.00863 0.00150 0.0011 0.5320 0.0699
0.000 0.0803 0.00848 0.00144 0.0019 0.5254 0.1000
0.250 0.1042 0.00835 0.00141 0.0028 0.5181 0.1370
0.500 0.1290 0.00824 0.00139 0.0034 0.5117 0.1644
0.750 0.1528 0.00810 0.00137 0.0043 0.5049 0.2094
1.000 0.1762 0.00793 0.00135 0.0052 0.4986 0.2668
1.250 0.1876 0.00702 0.00126 0.0084 0.4918 0.5251
1.500 0.1783 0.00584 0.00119 0.0167 0.4864 0.8462
1.750 0.2413 0.00576 0.00122 0.0087 0.4747 0.8925
2.000 0.3372 0.00621 0.00166 -0.0065 0.4528 0.9222
2.250 0.3746 0.00648 0.00189 -0.0084 0.4409 0.9300
2.500 0.3981 0.00663 0.00201 -0.0073 0.4319 0.9392
3.000 0.4601 0.00698 0.00229 -0.0086 0.4152 0.9450
3.250 0.4788 0.00711 0.00238 -0.0065 0.4048 0.9520
3.500 0.5094 0.00726 0.00248 -0.0072 0.3918 0.9529
3.750 0.5396 0.00741 0.00258 -0.0077 0.3784 0.9539
4.000 0.5692 0.00756 0.00269 -0.0082 0.3663 0.9552
4.250 0.5977 0.00773 0.00280 -0.0084 0.3514 0.9568
4.500 0.6235 0.00796 0.00294 -0.0081 0.3314 0.9595
4.750 0.6425 0.00815 0.00308 -0.0062 0.3169 0.9642
5.000 0.6722 0.00836 0.00323 -0.0068 0.2997 0.9650
5.250 0.7007 0.00866 0.00341 -0.0072 0.2732 0.9660
5.500 0.7282 0.00899 0.00362 -0.0074 0.2470 0.9673
5.750 0.7541 0.00936 0.00386 -0.0073 0.2189 0.9692
6.000 0.7755 0.00973 0.00412 -0.0061 0.1960 0.9726
6.250 0.7975 0.01008 0.00438 -0.0051 0.1767 0.9751
6.500 0.8262 0.01041 0.00463 -0.0056 0.1572 0.9759
6.750 0.8536 0.01081 0.00492 -0.0060 0.1338 0.9769
7.000 0.8786 0.01138 0.00531 -0.0059 0.0995 0.9782
7.250 0.9033 0.01187 0.00569 -0.0057 0.0803 0.9799
7.500 0.9276 0.01222 0.00601 -0.0053 0.0713 0.9819
7.750 0.9468 0.01262 0.00637 -0.0038 0.0621 0.9848
8.000 0.9751 0.01301 0.00670 -0.0044 0.0514 0.9854
8.250 1.0026 0.01343 0.00706 -0.0049 0.0423 0.9862
8.500 1.0299 0.01378 0.00740 -0.0052 0.0380 0.9871
8.750 1.0563 0.01416 0.00776 -0.0054 0.0344 0.9881
9.000 1.0824 0.01449 0.00811 -0.0055 0.0324 0.9893
9.250 1.1072 0.01486 0.00848 -0.0054 0.0305 0.9906
9.500 1.1303 0.01528 0.00890 -0.0050 0.0285 0.9920
9.750 1.1526 0.01567 0.00931 -0.0044 0.0272 0.9935
10.000 1.1773 0.01604 0.00971 -0.0043 0.0258 0.9945
10.250 1.2031 0.01644 0.01013 -0.0046 0.0245 0.9953
10.500 1.2270 0.01690 0.01060 -0.0045 0.0228 0.9962
10.750 1.2506 0.01728 0.01101 -0.0044 0.0220 0.9972
11.000 1.2729 0.01772 0.01148 -0.0040 0.0207 0.9982
11.250 1.2939 0.01821 0.01198 -0.0035 0.0195 0.9992
11.500 1.3117 0.01870 0.01249 -0.0024 0.0183 1.0000
11.750 1.3138 0.01913 0.01297 0.0019 0.0178 1.0000
12.000 1.3175 0.01966 0.01355 0.0057 0.0171 1.0000
12.250 1.3222 0.02030 0.01423 0.0089 0.0165 1.0000
12.500 1.3269 0.02107 0.01503 0.0119 0.0157 1.0000
12.750 1.3316 0.02197 0.01596 0.0146 0.0149 1.0000
13.000 1.3381 0.02287 0.01691 0.0168 0.0145 1.0000
13.250 1.3445 0.02386 0.01796 0.0188 0.0141 1.0000
13.500 1.3504 0.02498 0.01913 0.0207 0.0135 1.0000
13.750 1.3559 0.02621 0.02043 0.0224 0.0131 1.0000
14.000 1.3606 0.02760 0.02186 0.0239 0.0126 1.0000
14.250 1.3646 0.02914 0.02344 0.0253 0.0121 1.0000
14.500 1.3682 0.03078 0.02514 0.0264 0.0118 1.0000
14.750 1.3734 0.03238 0.02681 0.0274 0.0115 1.0000
15.000 1.3770 0.03417 0.02867 0.0283 0.0112 1.0000
15.250 1.3800 0.03607 0.03063 0.0290 0.0109 1.0000
15.500 1.3829 0.03804 0.03267 0.0297 0.0106 1.0000
15.750 1.3837 0.04026 0.03497 0.0302 0.0104 1.0000
16.000 1.3839 0.04260 0.03738 0.0306 0.0101 1.0000
16.250 1.3832 0.04508 0.03992 0.0309 0.0098 1.0000
16.500 1.3817 0.04774 0.04265 0.0311 0.0097 1.0000
16.750 1.3779 0.05073 0.04571 0.0310 0.0093 1.0000
17.000 1.3761 0.05360 0.04866 0.0309 0.0094 1.0000
17.250 1.3721 0.05682 0.05196 0.0306 0.0091 1.0000
17.500 1.3696 0.05992 0.05514 0.0302 0.0090 1.0000
17.750 1.3663 0.06318 0.05849 0.0296 0.0089 1.0000
18.000 1.3597 0.06699 0.06239 0.0289 0.0088 1.0000
18.250 1.3554 0.07055 0.06604 0.0281 0.0086 1.0000
18.500 1.3499 0.07433 0.06991 0.0271 0.0084 1.0000
18.750 1.3426 0.07843 0.07411 0.0260 0.0084 1.0000
19.000 1.3346 0.08273 0.07850 0.0248 0.0083 1.0000
19.250 1.3262 0.08715 0.08301 0.0234 0.0082 1.0000
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