NACA 67 (naca671215-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 67 (naca671215-il) Reynolds number: 500,000 Max Cl/Cd: 56.18 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca671215-il-500000.txt Download as CSV file: xf-naca671215-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 67
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5382 0.08779 0.08516 -0.0994 0.9785 0.0219
-14.750 -0.5588 0.07768 0.07499 -0.1072 0.9769 0.0213
-14.500 -0.6005 0.06453 0.06158 -0.1185 0.9746 0.0211
-14.250 -0.6351 0.05556 0.05231 -0.1246 0.9720 0.0207
-14.000 -0.6611 0.04969 0.04614 -0.1265 0.9671 0.0207
-13.750 -0.6859 0.04443 0.04053 -0.1267 0.9622 0.0208
-13.500 -0.6988 0.04102 0.03683 -0.1256 0.9573 0.0209
-13.250 -0.7157 0.03822 0.03372 -0.1223 0.9509 0.0213
-13.000 -0.7204 0.03589 0.03116 -0.1200 0.9465 0.0211
-12.750 -0.7284 0.03402 0.02901 -0.1163 0.9416 0.0215
-12.500 -0.7299 0.03235 0.02711 -0.1132 0.9373 0.0216
-12.250 -0.7293 0.03102 0.02553 -0.1101 0.9333 0.0218
-12.000 -0.7256 0.02921 0.02345 -0.1075 0.9303 0.0221
-11.750 -0.7114 0.02721 0.02130 -0.1064 0.9283 0.0225
-11.500 -0.6959 0.02601 0.02002 -0.1053 0.9259 0.0229
-11.250 -0.6807 0.02521 0.01915 -0.1040 0.9236 0.0232
-11.000 -0.6649 0.02449 0.01835 -0.1027 0.9214 0.0238
-10.750 -0.6480 0.02378 0.01754 -0.1015 0.9195 0.0243
-10.500 -0.6293 0.02305 0.01670 -0.1005 0.9179 0.0252
-10.250 -0.6107 0.02247 0.01600 -0.0995 0.9163 0.0260
-10.000 -0.5921 0.02196 0.01537 -0.0984 0.9147 0.0265
-9.750 -0.5642 0.02064 0.01399 -0.0990 0.9139 0.0275
-9.500 -0.5448 0.02010 0.01347 -0.0982 0.9121 0.0285
-9.250 -0.5250 0.01962 0.01296 -0.0973 0.9102 0.0294
-9.000 -0.5051 0.01920 0.01248 -0.0964 0.9085 0.0307
-8.750 -0.4845 0.01880 0.01201 -0.0955 0.9070 0.0319
-8.500 -0.4649 0.01803 0.01121 -0.0946 0.9057 0.0335
-8.250 -0.4456 0.01767 0.01087 -0.0936 0.9044 0.0353
-8.000 -0.4255 0.01737 0.01054 -0.0926 0.9031 0.0374
-7.750 -0.4045 0.01716 0.01026 -0.0917 0.9020 0.0390
-7.500 -0.3889 0.01651 0.00962 -0.0901 0.9007 0.0415
-7.250 -0.3701 0.01627 0.00939 -0.0889 0.8995 0.0438
-7.000 -0.3510 0.01607 0.00916 -0.0877 0.8979 0.0459
-6.750 -0.3347 0.01574 0.00880 -0.0860 0.8960 0.0482
-6.500 -0.3185 0.01543 0.00852 -0.0844 0.8943 0.0511
-6.250 -0.3001 0.01526 0.00835 -0.0830 0.8928 0.0544
-6.000 -0.2817 0.01509 0.00814 -0.0816 0.8913 0.0570
-5.750 -0.2661 0.01479 0.00787 -0.0797 0.8899 0.0619
-5.500 -0.2476 0.01461 0.00768 -0.0783 0.8886 0.0671
-5.250 -0.2313 0.01430 0.00741 -0.0764 0.8872 0.0768
-5.000 -0.2162 0.01399 0.00721 -0.0743 0.8859 0.0989
-4.750 -0.2104 0.01367 0.00718 -0.0705 0.8842 0.1575
-4.500 -0.2216 0.01382 0.00756 -0.0634 0.8800 0.2070
-4.250 -0.2325 0.01380 0.00777 -0.0561 0.8759 0.2624
-4.000 -0.2387 0.01342 0.00775 -0.0497 0.8733 0.3487
-3.750 -0.2451 0.01273 0.00751 -0.0431 0.8711 0.4622
-3.500 -0.2762 0.01337 0.00829 -0.0317 0.8637 0.4938
-3.250 -0.2958 0.01295 0.00832 -0.0224 0.8587 0.5969
-3.000 -0.2858 0.01261 0.00865 -0.0183 0.8571 0.7510
-2.750 -0.2573 0.01278 0.00880 -0.0182 0.8564 0.7816
-2.500 -0.2282 0.01298 0.00896 -0.0184 0.8558 0.7968
-2.250 -0.2316 0.01353 0.00949 -0.0122 0.8507 0.8053
-2.000 -0.1866 0.01364 0.00957 -0.0155 0.8519 0.8139
-1.750 -0.1451 0.01378 0.00968 -0.0180 0.8529 0.8241
-1.500 -0.1002 0.01440 0.01034 -0.0205 0.8538 0.8338
-1.250 -0.1480 0.01500 0.01094 -0.0057 0.8412 0.8421
-1.000 -0.1132 0.01618 0.01218 -0.0055 0.8408 0.8558
-0.750 -0.0694 0.01736 0.01341 -0.0071 0.8407 0.8625
-0.500 -0.0307 0.01757 0.01360 -0.0092 0.8404 0.8645
-0.250 -0.0717 0.01762 0.01363 0.0037 0.8290 0.8741
0.000 -0.0412 0.01751 0.01351 0.0031 0.8276 0.8750
0.250 -0.0083 0.01739 0.01337 0.0019 0.8267 0.8758
0.500 0.0264 0.01724 0.01320 0.0004 0.8259 0.8766
0.750 0.0624 0.01707 0.01302 -0.0014 0.8253 0.8772
1.000 0.1005 0.01687 0.01282 -0.0036 0.8249 0.8777
1.250 0.1396 0.01664 0.01259 -0.0060 0.8246 0.8782
1.500 0.1826 0.01633 0.01228 -0.0091 0.8243 0.8784
1.750 0.2280 0.01598 0.01194 -0.0128 0.8241 0.8785
2.000 0.2737 0.01555 0.01153 -0.0164 0.8238 0.8787
2.250 0.3115 0.01509 0.01108 -0.0183 0.8211 0.8791
2.500 0.3171 0.01483 0.01084 -0.0138 0.8127 0.8817
2.750 0.3908 0.01371 0.00973 -0.0225 0.8122 0.8799
3.000 0.4754 0.01224 0.00820 -0.0334 0.8074 0.8777
3.250 0.4837 0.01199 0.00801 -0.0292 0.7973 0.8799
3.500 0.5186 0.01151 0.00753 -0.0304 0.7898 0.8807
3.750 0.5288 0.01124 0.00730 -0.0269 0.7807 0.8829
4.000 0.5386 0.01093 0.00702 -0.0233 0.7704 0.8856
4.250 0.5425 0.01057 0.00668 -0.0186 0.7566 0.8889
4.500 0.5418 0.01029 0.00642 -0.0127 0.7395 0.8909
4.750 0.5607 0.00998 0.00602 -0.0106 0.7020 0.8920
5.000 0.5651 0.01015 0.00578 -0.0056 0.6219 0.8938
5.250 0.5506 0.01078 0.00608 0.0026 0.5510 0.8971
5.500 0.5388 0.01152 0.00649 0.0097 0.4823 0.9001
5.750 0.5324 0.01233 0.00695 0.0154 0.4077 0.9029
6.000 0.5324 0.01317 0.00741 0.0197 0.3309 0.9050
6.250 0.5338 0.01391 0.00781 0.0240 0.2575 0.9071
6.500 0.5409 0.01463 0.00821 0.0271 0.1895 0.9088
6.750 0.5502 0.01536 0.00864 0.0297 0.1285 0.9105
7.000 0.5626 0.01601 0.00906 0.0318 0.0873 0.9122
7.250 0.5785 0.01653 0.00946 0.0333 0.0695 0.9138
7.500 0.5965 0.01695 0.00986 0.0345 0.0613 0.9154
7.750 0.6128 0.01749 0.01036 0.0359 0.0550 0.9171
8.000 0.6328 0.01783 0.01073 0.0367 0.0518 0.9186
8.250 0.6512 0.01825 0.01115 0.0377 0.0486 0.9202
8.500 0.6648 0.01882 0.01173 0.0396 0.0451 0.9221
8.750 0.6836 0.01915 0.01211 0.0407 0.0430 0.9239
9.000 0.7012 0.01957 0.01257 0.0419 0.0409 0.9257
9.250 0.7158 0.02019 0.01319 0.0434 0.0384 0.9279
9.500 0.7321 0.02075 0.01380 0.0447 0.0364 0.9300
9.750 0.7501 0.02122 0.01431 0.0457 0.0343 0.9321
10.000 0.7669 0.02178 0.01487 0.0467 0.0324 0.9342
10.250 0.7786 0.02262 0.01574 0.0487 0.0306 0.9365
10.500 0.7953 0.02311 0.01632 0.0499 0.0291 0.9391
10.750 0.8124 0.02355 0.01678 0.0509 0.0272 0.9419
11.000 0.8253 0.02442 0.01765 0.0524 0.0259 0.9449
11.250 0.8399 0.02529 0.01859 0.0538 0.0250 0.9479
11.500 0.8558 0.02589 0.01929 0.0549 0.0241 0.9515
11.750 0.8711 0.02658 0.02006 0.0561 0.0232 0.9554
12.000 0.8865 0.02739 0.02093 0.0571 0.0226 0.9594
12.250 0.9038 0.02818 0.02175 0.0575 0.0217 0.9632
12.500 0.9227 0.02942 0.02305 0.0577 0.0213 0.9665
12.750 0.9429 0.03078 0.02453 0.0576 0.0207 0.9698
13.000 0.9635 0.03194 0.02584 0.0572 0.0204 0.9734
13.250 0.9845 0.03332 0.02738 0.0565 0.0198 0.9765
13.500 1.0044 0.03472 0.02892 0.0557 0.0193 0.9799
13.750 1.0228 0.03620 0.03053 0.0550 0.0189 0.9835
14.000 1.0386 0.03763 0.03207 0.0544 0.0184 0.9915
14.250 1.0484 0.03937 0.03393 0.0551 0.0182 1.0000
14.500 1.0554 0.04088 0.03554 0.0561 0.0180 1.0000
14.750 1.0611 0.04258 0.03733 0.0571 0.0177 1.0000
15.000 1.0650 0.04461 0.03947 0.0581 0.0176 1.0000
15.250 1.0655 0.04724 0.04223 0.0592 0.0173 1.0000
15.500 1.0604 0.05040 0.04558 0.0604 0.0172 1.0000
15.750 1.0496 0.05414 0.04955 0.0615 0.0171 1.0000
16.000 1.0364 0.05790 0.05352 0.0622 0.0170 1.0000
16.250 1.0243 0.06182 0.05763 0.0625 0.0170 1.0000
16.500 1.0081 0.06637 0.06239 0.0621 0.0170 1.0000
16.750 0.9891 0.07161 0.06784 0.0610 0.0169 1.0000
17.000 0.9674 0.07780 0.07423 0.0592 0.0170 1.0000
17.250 0.9450 0.08456 0.08117 0.0563 0.0170 1.0000
17.500 0.9188 0.09258 0.08939 0.0522 0.0170 1.0000
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