NACA 0010 (naca0010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 100,000 Max Cl/Cd: 33.51 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0010-il-100000-n5.txt Download as CSV file: xf-naca0010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7784 0.09853 0.09336 0.0003 1.0000 0.0361
-11.750 -0.8751 0.07116 0.06575 -0.0210 1.0000 0.0324
-11.500 -0.9141 0.06246 0.05674 -0.0267 1.0000 0.0318
-11.250 -0.9337 0.05792 0.05197 -0.0274 1.0000 0.0320
-11.000 -0.9465 0.05463 0.04847 -0.0263 1.0000 0.0324
-10.750 -0.9536 0.05181 0.04544 -0.0247 1.0000 0.0331
-10.500 -0.9554 0.04902 0.04239 -0.0232 1.0000 0.0342
-10.250 -0.9559 0.04597 0.03897 -0.0216 1.0000 0.0356
-10.000 -0.9537 0.04279 0.03532 -0.0198 1.0000 0.0369
-9.750 -0.9471 0.03983 0.03182 -0.0181 1.0000 0.0381
-9.500 -0.9344 0.03741 0.02923 -0.0169 1.0000 0.0397
-9.250 -0.9180 0.03598 0.02773 -0.0160 1.0000 0.0417
-9.000 -0.9014 0.03432 0.02580 -0.0149 1.0000 0.0439
-8.750 -0.8836 0.03245 0.02361 -0.0138 1.0000 0.0460
-8.500 -0.8644 0.03092 0.02171 -0.0127 1.0000 0.0484
-8.250 -0.8449 0.02930 0.02010 -0.0119 1.0000 0.0509
-8.000 -0.8241 0.02803 0.01874 -0.0110 1.0000 0.0532
-7.750 -0.8027 0.02686 0.01741 -0.0101 1.0000 0.0562
-7.500 -0.7806 0.02580 0.01608 -0.0092 1.0000 0.0592
-7.250 -0.7599 0.02450 0.01479 -0.0083 1.0000 0.0618
-7.000 -0.7387 0.02348 0.01375 -0.0073 1.0000 0.0645
-6.750 -0.7171 0.02259 0.01277 -0.0063 1.0000 0.0683
-6.500 -0.6955 0.02174 0.01183 -0.0053 1.0000 0.0728
-6.250 -0.6751 0.02084 0.01093 -0.0042 1.0000 0.0778
-6.000 -0.6537 0.02006 0.01007 -0.0031 1.0000 0.0839
-5.750 -0.6331 0.01922 0.00928 -0.0020 1.0000 0.0920
-5.500 -0.6120 0.01846 0.00855 -0.0009 1.0000 0.1043
-5.250 -0.5908 0.01774 0.00790 0.0002 1.0000 0.1248
-5.000 -0.5698 0.01703 0.00734 0.0012 1.0000 0.1544
-4.750 -0.5486 0.01637 0.00685 0.0022 1.0000 0.1905
-4.500 -0.5273 0.01578 0.00644 0.0032 1.0000 0.2324
-4.250 -0.5062 0.01519 0.00608 0.0043 1.0000 0.2846
-4.000 -0.4856 0.01461 0.00581 0.0054 1.0000 0.3474
-3.750 -0.4647 0.01412 0.00559 0.0066 1.0000 0.4083
-3.500 -0.4429 0.01373 0.00538 0.0078 1.0000 0.4584
-3.250 -0.4208 0.01341 0.00522 0.0090 1.0000 0.5041
-3.000 -0.3986 0.01311 0.00509 0.0102 1.0000 0.5503
-2.750 -0.3763 0.01286 0.00501 0.0114 1.0000 0.5965
-2.500 -0.3538 0.01265 0.00495 0.0127 1.0000 0.6422
-2.250 -0.3310 0.01249 0.00494 0.0140 1.0000 0.6857
-2.000 -0.3077 0.01239 0.00496 0.0153 1.0000 0.7269
-1.750 -0.2847 0.01233 0.00501 0.0166 1.0000 0.7668
-1.500 -0.2611 0.01234 0.00510 0.0179 1.0000 0.8051
-1.250 -0.2362 0.01239 0.00522 0.0188 1.0000 0.8420
-1.000 -0.1959 0.01251 0.00535 0.0166 0.9941 0.8751
-0.750 -0.1497 0.01263 0.00546 0.0131 0.9856 0.9025
-0.500 -0.1007 0.01272 0.00554 0.0090 0.9767 0.9237
-0.250 -0.0505 0.01278 0.00559 0.0045 0.9669 0.9412
0.000 0.0000 0.01280 0.00560 0.0000 0.9554 0.9554
0.250 0.0505 0.01278 0.00559 -0.0045 0.9412 0.9669
0.500 0.1007 0.01272 0.00554 -0.0090 0.9237 0.9767
0.750 0.1497 0.01263 0.00546 -0.0131 0.9025 0.9856
1.000 0.1959 0.01251 0.00535 -0.0166 0.8751 0.9941
1.250 0.2362 0.01239 0.00522 -0.0188 0.8420 1.0000
1.500 0.2611 0.01234 0.00510 -0.0179 0.8052 1.0000
1.750 0.2846 0.01233 0.00501 -0.0166 0.7668 1.0000
2.000 0.3077 0.01239 0.00496 -0.0153 0.7269 1.0000
2.250 0.3310 0.01249 0.00494 -0.0140 0.6857 1.0000
2.500 0.3538 0.01265 0.00495 -0.0127 0.6422 1.0000
2.750 0.3763 0.01286 0.00501 -0.0114 0.5965 1.0000
3.000 0.3986 0.01311 0.00509 -0.0102 0.5503 1.0000
3.250 0.4208 0.01340 0.00522 -0.0090 0.5041 1.0000
3.500 0.4429 0.01373 0.00538 -0.0078 0.4584 1.0000
3.750 0.4646 0.01412 0.00559 -0.0066 0.4083 1.0000
4.000 0.4855 0.01461 0.00581 -0.0054 0.3474 1.0000
4.250 0.5062 0.01519 0.00608 -0.0043 0.2847 1.0000
4.500 0.5272 0.01578 0.00643 -0.0032 0.2324 1.0000
4.750 0.5486 0.01637 0.00685 -0.0022 0.1905 1.0000
5.000 0.5698 0.01703 0.00734 -0.0012 0.1544 1.0000
5.250 0.5908 0.01774 0.00790 -0.0002 0.1248 1.0000
5.500 0.6120 0.01846 0.00855 0.0009 0.1043 1.0000
5.750 0.6331 0.01922 0.00928 0.0020 0.0920 1.0000
6.000 0.6537 0.02006 0.01007 0.0031 0.0839 1.0000
6.250 0.6751 0.02084 0.01093 0.0042 0.0778 1.0000
6.500 0.6956 0.02173 0.01183 0.0053 0.0729 1.0000
6.750 0.7171 0.02259 0.01277 0.0063 0.0683 1.0000
7.000 0.7387 0.02348 0.01374 0.0073 0.0645 1.0000
7.250 0.7599 0.02450 0.01479 0.0083 0.0618 1.0000
7.500 0.7806 0.02580 0.01608 0.0092 0.0592 1.0000
7.750 0.8028 0.02686 0.01741 0.0101 0.0562 1.0000
8.000 0.8241 0.02803 0.01874 0.0110 0.0532 1.0000
8.250 0.8449 0.02930 0.02010 0.0119 0.0509 1.0000
8.500 0.8644 0.03092 0.02171 0.0126 0.0484 1.0000
8.750 0.8836 0.03245 0.02361 0.0138 0.0460 1.0000
9.000 0.9015 0.03432 0.02580 0.0149 0.0439 1.0000
9.250 0.9181 0.03598 0.02773 0.0160 0.0417 1.0000
9.500 0.9345 0.03741 0.02923 0.0169 0.0397 1.0000
9.750 0.9472 0.03984 0.03183 0.0180 0.0381 1.0000
10.000 0.9538 0.04280 0.03533 0.0198 0.0369 1.0000
10.250 0.9560 0.04598 0.03898 0.0216 0.0356 1.0000
10.500 0.9556 0.04904 0.04241 0.0232 0.0342 1.0000
10.750 0.9538 0.05183 0.04546 0.0246 0.0331 1.0000
11.000 0.9469 0.05465 0.04849 0.0262 0.0324 1.0000
11.250 0.9342 0.05793 0.05197 0.0273 0.0319 1.0000
11.500 0.9145 0.06251 0.05678 0.0265 0.0318 1.0000
11.750 0.8751 0.07130 0.06590 0.0208 0.0324 1.0000
12.000 0.7786 0.09881 0.09365 -0.0006 0.0361 1.0000
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Polar data table (+)
Polar graphs
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