NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-65 (naca001065-il) Reynolds number: 1,000,000 Max Cl/Cd: 57.44 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001065-il-1000000.txt Download as CSV file: xf-naca001065-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-65
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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0187 0.09102 0.08900 -0.0346 1.0000 0.0095
-16.250 -1.1350 0.05932 0.05687 -0.0560 1.0000 0.0090
-16.000 -1.1656 0.05126 0.04859 -0.0604 1.0000 0.0090
-15.750 -1.1845 0.04628 0.04342 -0.0613 1.0000 0.0090
-15.500 -1.1965 0.04271 0.03969 -0.0609 1.0000 0.0091
-15.250 -1.2051 0.03982 0.03663 -0.0596 1.0000 0.0092
-15.000 -1.2088 0.03760 0.03427 -0.0578 1.0000 0.0092
-14.750 -1.2090 0.03582 0.03235 -0.0559 1.0000 0.0093
-14.500 -1.2152 0.03368 0.03005 -0.0530 1.0000 0.0094
-14.250 -1.2337 0.03086 0.02698 -0.0482 1.0000 0.0097
-14.000 -1.2404 0.02916 0.02514 -0.0439 1.0000 0.0099
-13.750 -1.2410 0.02805 0.02393 -0.0400 1.0000 0.0101
-13.500 -1.2397 0.02721 0.02302 -0.0360 1.0000 0.0103
-13.250 -1.2385 0.02656 0.02230 -0.0317 1.0000 0.0105
-13.000 -1.2398 0.02602 0.02169 -0.0267 1.0000 0.0107
-12.750 -1.2424 0.02553 0.02113 -0.0213 1.0000 0.0109
-12.500 -1.2388 0.02494 0.02046 -0.0171 1.0000 0.0112
-12.250 -1.2329 0.02433 0.01976 -0.0134 1.0000 0.0114
-12.000 -1.2259 0.02369 0.01901 -0.0098 1.0000 0.0117
-11.750 -1.2174 0.02307 0.01830 -0.0065 1.0000 0.0120
-11.500 -1.2072 0.02251 0.01763 -0.0034 1.0000 0.0122
-11.250 -1.1943 0.02154 0.01652 -0.0011 0.9997 0.0126
-11.000 -1.1728 0.02043 0.01533 -0.0007 0.9987 0.0133
-10.750 -1.1457 0.02004 0.01491 -0.0012 0.9977 0.0138
-10.500 -1.1179 0.01973 0.01456 -0.0017 0.9967 0.0144
-10.250 -1.0899 0.01940 0.01418 -0.0023 0.9959 0.0151
-10.000 -1.0617 0.01909 0.01380 -0.0029 0.9951 0.0157
-9.750 -1.0352 0.01839 0.01298 -0.0032 0.9945 0.0163
-9.500 -1.0113 0.01762 0.01218 -0.0030 0.9934 0.0172
-9.250 -0.9851 0.01739 0.01193 -0.0031 0.9918 0.0179
-9.000 -0.9579 0.01713 0.01165 -0.0033 0.9904 0.0186
-8.750 -0.9303 0.01683 0.01130 -0.0037 0.9891 0.0195
-8.500 -0.9012 0.01668 0.01110 -0.0043 0.9880 0.0202
-8.250 -0.8749 0.01586 0.01019 -0.0045 0.9870 0.0212
-8.000 -0.8467 0.01533 0.00964 -0.0051 0.9861 0.0222
-7.750 -0.8168 0.01503 0.00934 -0.0059 0.9853 0.0232
-7.500 -0.7867 0.01473 0.00901 -0.0068 0.9847 0.0242
-7.250 -0.7559 0.01448 0.00873 -0.0078 0.9841 0.0252
-7.000 -0.7240 0.01433 0.00854 -0.0090 0.9836 0.0259
-6.750 -0.7052 0.01373 0.00788 -0.0073 0.9804 0.0266
-6.500 -0.6824 0.01295 0.00705 -0.0065 0.9783 0.0281
-6.250 -0.6544 0.01260 0.00670 -0.0069 0.9768 0.0292
-6.000 -0.6251 0.01228 0.00637 -0.0075 0.9756 0.0304
-5.750 -0.5954 0.01195 0.00601 -0.0082 0.9746 0.0314
-5.500 -0.5647 0.01167 0.00571 -0.0091 0.9738 0.0324
-5.250 -0.5332 0.01143 0.00545 -0.0101 0.9731 0.0331
-5.000 -0.5027 0.01098 0.00495 -0.0110 0.9725 0.0343
-4.750 -0.4715 0.01059 0.00454 -0.0119 0.9719 0.0363
-4.500 -0.4393 0.01031 0.00427 -0.0132 0.9714 0.0383
-4.250 -0.4071 0.01008 0.00403 -0.0143 0.9709 0.0402
-4.000 -0.3919 0.00994 0.00388 -0.0115 0.9656 0.0415
-3.750 -0.3632 0.00968 0.00363 -0.0119 0.9639 0.0463
-3.500 -0.3342 0.00938 0.00343 -0.0123 0.9624 0.0604
-3.250 -0.3051 0.00906 0.00324 -0.0128 0.9611 0.0899
-3.000 -0.2759 0.00873 0.00307 -0.0134 0.9599 0.1242
-2.750 -0.2471 0.00840 0.00291 -0.0139 0.9588 0.1677
-2.500 -0.2188 0.00802 0.00276 -0.0142 0.9576 0.2263
-2.250 -0.2021 0.00761 0.00266 -0.0120 0.9533 0.3082
-2.000 -0.1866 0.00687 0.00246 -0.0097 0.9493 0.4573
-1.750 -0.1764 0.00582 0.00218 -0.0061 0.9459 0.6643
-1.500 -0.1576 0.00531 0.00209 -0.0039 0.9437 0.7748
-1.250 -0.1362 0.00517 0.00213 -0.0023 0.9405 0.8257
-1.000 -0.1127 0.00512 0.00217 -0.0012 0.9369 0.8557
-0.750 -0.0840 0.00502 0.00214 -0.0011 0.9334 0.8768
-0.500 -0.0512 0.00485 0.00198 -0.0018 0.9284 0.8910
-0.250 -0.0277 0.00483 0.00197 -0.0004 0.9206 0.9032
0.000 0.0000 0.00479 0.00192 0.0000 0.9140 0.9140
0.250 0.0278 0.00483 0.00198 0.0004 0.9032 0.9206
0.500 0.0513 0.00485 0.00198 0.0017 0.8912 0.9283
0.750 0.0840 0.00502 0.00214 0.0011 0.8769 0.9334
1.000 0.1127 0.00512 0.00217 0.0012 0.8557 0.9369
1.250 0.1362 0.00517 0.00213 0.0023 0.8254 0.9405
1.500 0.1577 0.00530 0.00209 0.0039 0.7753 0.9437
1.750 0.1767 0.00581 0.00218 0.0060 0.6667 0.9459
2.000 0.1868 0.00686 0.00245 0.0096 0.4595 0.9493
2.250 0.2021 0.00761 0.00266 0.0120 0.3080 0.9533
2.500 0.2188 0.00802 0.00276 0.0142 0.2267 0.9576
2.750 0.2471 0.00840 0.00291 0.0139 0.1681 0.9588
3.000 0.2759 0.00873 0.00307 0.0134 0.1244 0.9599
3.250 0.3051 0.00906 0.00324 0.0128 0.0898 0.9611
3.500 0.3342 0.00938 0.00343 0.0123 0.0605 0.9624
3.750 0.3632 0.00968 0.00363 0.0119 0.0463 0.9639
4.000 0.3919 0.00994 0.00388 0.0115 0.0415 0.9656
4.250 0.4071 0.01008 0.00403 0.0143 0.0402 0.9709
4.500 0.4392 0.01031 0.00427 0.0132 0.0383 0.9714
4.750 0.4715 0.01059 0.00454 0.0120 0.0362 0.9719
5.000 0.5027 0.01098 0.00496 0.0109 0.0343 0.9725
5.250 0.5332 0.01143 0.00545 0.0101 0.0331 0.9731
5.500 0.5647 0.01167 0.00571 0.0090 0.0324 0.9738
5.750 0.5954 0.01195 0.00601 0.0082 0.0314 0.9746
6.000 0.6251 0.01228 0.00637 0.0075 0.0304 0.9756
6.250 0.6544 0.01260 0.00670 0.0069 0.0293 0.9768
6.500 0.6823 0.01295 0.00705 0.0066 0.0281 0.9783
6.750 0.7052 0.01371 0.00785 0.0072 0.0267 0.9804
7.000 0.7240 0.01433 0.00854 0.0090 0.0259 0.9836
7.250 0.7558 0.01448 0.00872 0.0078 0.0252 0.9841
7.500 0.7868 0.01473 0.00900 0.0068 0.0242 0.9847
7.750 0.8168 0.01504 0.00934 0.0059 0.0232 0.9853
8.000 0.8468 0.01532 0.00964 0.0051 0.0222 0.9861
8.250 0.8750 0.01586 0.01018 0.0045 0.0212 0.9870
8.500 0.9012 0.01669 0.01112 0.0043 0.0202 0.9880
8.750 0.9303 0.01684 0.01131 0.0037 0.0195 0.9891
9.000 0.9579 0.01713 0.01165 0.0033 0.0186 0.9904
9.250 0.9850 0.01739 0.01193 0.0031 0.0179 0.9918
9.500 1.0112 0.01762 0.01218 0.0030 0.0172 0.9934
9.750 1.0354 0.01836 0.01296 0.0032 0.0163 0.9945
10.000 1.0618 0.01908 0.01379 0.0028 0.0157 0.9951
10.250 1.0901 0.01939 0.01417 0.0023 0.0151 0.9959
10.500 1.1181 0.01972 0.01455 0.0017 0.0144 0.9967
10.750 1.1459 0.02003 0.01489 0.0011 0.0138 0.9977
11.000 1.1730 0.02042 0.01531 0.0007 0.0133 0.9987
11.250 1.1944 0.02154 0.01653 0.0011 0.0126 0.9997
11.500 1.2072 0.02251 0.01764 0.0034 0.0122 1.0000
11.750 1.2174 0.02306 0.01829 0.0064 0.0120 1.0000
12.000 1.2261 0.02367 0.01900 0.0097 0.0117 1.0000
12.250 1.2330 0.02431 0.01974 0.0133 0.0114 1.0000
12.500 1.2386 0.02495 0.02048 0.0171 0.0112 1.0000
12.750 1.2423 0.02554 0.02114 0.0213 0.0109 1.0000
13.000 1.2401 0.02601 0.02168 0.0267 0.0107 1.0000
13.250 1.2383 0.02658 0.02232 0.0318 0.0105 1.0000
13.500 1.2396 0.02722 0.02303 0.0360 0.0103 1.0000
13.750 1.2415 0.02803 0.02392 0.0399 0.0101 1.0000
14.000 1.2410 0.02914 0.02511 0.0438 0.0099 1.0000
14.250 1.2344 0.03084 0.02696 0.0480 0.0097 1.0000
14.500 1.2156 0.03371 0.03008 0.0529 0.0094 1.0000
14.750 1.2110 0.03573 0.03226 0.0556 0.0093 1.0000
15.000 1.2093 0.03765 0.03432 0.0577 0.0092 1.0000
15.250 1.2066 0.03979 0.03660 0.0594 0.0091 1.0000
15.500 1.1984 0.04265 0.03962 0.0606 0.0091 1.0000
15.750 1.1862 0.04624 0.04338 0.0611 0.0090 1.0000
16.000 1.1673 0.05123 0.04856 0.0601 0.0090 1.0000
16.250 1.1368 0.05930 0.05685 0.0558 0.0090 1.0000
16.500 1.0187 0.09146 0.08943 0.0340 0.0096 1.0000
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