NACA 66 (p51hroot-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 200,000 Max Cl/Cd: 42.36 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51hroot-il-200000.txt Download as CSV file: xf-p51hroot-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2820 0.09434 0.09085 -0.0833 0.9426 0.0786
-12.000 -0.2903 0.08921 0.08572 -0.0858 0.9395 0.0818
-11.750 -0.3364 0.07747 0.07401 -0.0947 0.9374 0.0843
-11.500 -0.4440 0.07499 0.07136 -0.1005 0.9575 0.0776
-11.250 -0.4672 0.06960 0.06587 -0.1035 0.9494 0.0781
-11.000 -0.4889 0.06566 0.06180 -0.1040 0.9419 0.0791
-10.750 -0.5122 0.06263 0.05863 -0.1026 0.9339 0.0807
-10.500 -0.5331 0.06020 0.05604 -0.1001 0.9265 0.0814
-10.250 -0.5684 0.05939 0.05497 -0.0939 0.9177 0.0838
-10.000 -0.6112 0.06213 0.05721 -0.0855 0.9094 0.0856
-9.000 -0.6171 0.03896 0.03222 -0.0732 0.8957 0.0500
-8.750 -0.6034 0.03630 0.02931 -0.0718 0.8928 0.0491
-8.500 -0.5876 0.03416 0.02687 -0.0703 0.8902 0.0488
-8.250 -0.5676 0.03205 0.02447 -0.0693 0.8881 0.0485
-8.000 -0.5439 0.03023 0.02238 -0.0687 0.8863 0.0485
-7.750 -0.5187 0.02882 0.02073 -0.0684 0.8847 0.0493
-7.500 -0.4970 0.02813 0.01983 -0.0677 0.8824 0.0506
-7.250 -0.4705 0.02711 0.01866 -0.0679 0.8804 0.0514
-7.000 -0.4246 0.02495 0.01653 -0.0716 0.8799 0.0531
-6.750 -0.3948 0.02412 0.01573 -0.0725 0.8784 0.0553
-6.500 -0.3682 0.02354 0.01514 -0.0728 0.8766 0.0578
-6.250 -0.3424 0.02295 0.01452 -0.0729 0.8750 0.0596
-6.000 -0.3220 0.02257 0.01409 -0.0719 0.8733 0.0614
-5.750 -0.3085 0.02189 0.01346 -0.0699 0.8714 0.0637
-5.500 -0.2966 0.02157 0.01316 -0.0673 0.8695 0.0671
-5.250 -0.2841 0.02146 0.01300 -0.0649 0.8678 0.0713
-5.000 -0.2903 0.02192 0.01345 -0.0597 0.8642 0.0737
-4.750 -0.2994 0.02223 0.01378 -0.0537 0.8606 0.0768
-4.500 -0.2977 0.02229 0.01383 -0.0494 0.8577 0.0827
-4.250 -0.2954 0.02223 0.01381 -0.0451 0.8557 0.0950
-4.000 -0.3031 0.02138 0.01359 -0.0394 0.8537 0.2011
-3.750 -0.3233 0.01955 0.01318 -0.0314 0.8516 0.4861
-3.500 -0.3580 0.02100 0.01417 -0.0206 0.8468 0.4052
-3.250 -0.3801 0.02038 0.01478 -0.0114 0.8443 0.6310
-3.000 -0.3705 0.02099 0.01553 -0.0072 0.8419 0.7301
-2.750 -0.3521 0.02169 0.01623 -0.0047 0.8401 0.7589
-2.500 -0.3307 0.02233 0.01681 -0.0030 0.8384 0.7815
-2.250 -0.3022 0.02347 0.01800 -0.0012 0.8369 0.8035
-2.000 -0.2696 0.02503 0.01958 0.0007 0.8357 0.8283
-1.750 -0.2828 0.02579 0.02036 0.0084 0.8313 0.8393
-1.500 -0.2767 0.02656 0.02112 0.0132 0.8279 0.8534
-1.250 -0.2567 0.02734 0.02187 0.0157 0.8251 0.8676
-1.000 -0.2119 0.02821 0.02268 0.0134 0.8232 0.8746
-0.750 -0.1966 0.02795 0.02234 0.0151 0.8207 0.8818
-0.500 -0.1521 0.02817 0.02249 0.0119 0.8193 0.8832
-0.250 -0.1615 0.02835 0.02267 0.0179 0.8123 0.8884
0.000 -0.1459 0.02830 0.02258 0.0195 0.8082 0.8928
0.250 -0.1259 0.02807 0.02228 0.0204 0.8050 0.8981
0.500 -0.0852 0.02815 0.02233 0.0178 0.8032 0.8990
0.750 -0.0421 0.02827 0.02240 0.0147 0.8016 0.8996
1.000 -0.0615 0.02825 0.02240 0.0220 0.7911 0.9051
1.250 -0.0271 0.02823 0.02236 0.0205 0.7884 0.9069
1.500 0.0127 0.02823 0.02233 0.0181 0.7865 0.9080
1.750 -0.0016 0.02804 0.02214 0.0244 0.7760 0.9144
2.000 0.0335 0.02806 0.02216 0.0228 0.7729 0.9159
2.250 0.0800 0.02791 0.02201 0.0196 0.7706 0.9165
2.500 0.0902 0.02787 0.02199 0.0221 0.7598 0.9201
2.750 0.1527 0.02694 0.02106 0.0172 0.7554 0.9192
3.000 0.1985 0.02662 0.02077 0.0141 0.7539 0.9198
3.250 0.2009 0.02654 0.02071 0.0180 0.7419 0.9254
3.500 0.2529 0.02577 0.01999 0.0145 0.7394 0.9257
3.750 0.2761 0.02544 0.01969 0.0153 0.7340 0.9295
4.000 0.3695 0.02387 0.01822 0.0055 0.7363 0.9245
4.250 0.3591 0.02399 0.01838 0.0115 0.7239 0.9315
4.500 0.4257 0.02235 0.01682 0.0063 0.7230 0.9303
4.750 0.4821 0.02066 0.01522 0.0028 0.7165 0.9300
5.000 0.6023 0.01715 0.01178 -0.0104 0.7035 0.9223
5.250 0.6017 0.01639 0.01106 -0.0046 0.6864 0.9288
5.500 0.6001 0.01611 0.01088 0.0008 0.6645 0.9343
5.750 0.5965 0.01591 0.01074 0.0066 0.6426 0.9425
6.000 0.6253 0.01476 0.00872 0.0085 0.4828 0.9453
6.250 0.6083 0.01608 0.00941 0.0152 0.3710 0.9543
6.500 0.5894 0.01822 0.01073 0.0205 0.2244 0.9640
6.750 0.5838 0.02042 0.01209 0.0233 0.0856 0.9724
7.000 0.6060 0.02176 0.01325 0.0223 0.0605 0.9757
7.250 0.6317 0.02273 0.01426 0.0211 0.0555 0.9795
7.500 0.6558 0.02369 0.01525 0.0201 0.0527 0.9840
7.750 0.6799 0.02496 0.01650 0.0187 0.0503 0.9873
8.000 0.7071 0.02592 0.01751 0.0173 0.0486 0.9913
8.250 0.7351 0.02688 0.01851 0.0160 0.0474 0.9955
8.500 0.7659 0.02785 0.01949 0.0144 0.0461 0.9993
8.750 0.7659 0.02809 0.01973 0.0183 0.0454 1.0000
9.000 0.7616 0.02819 0.01982 0.0231 0.0446 1.0000
9.250 0.7818 0.02887 0.02041 0.0241 0.0433 1.0000
9.500 0.8269 0.03010 0.02160 0.0221 0.0424 1.0000
9.750 0.8529 0.03100 0.02263 0.0223 0.0417 1.0000
10.000 0.8808 0.03209 0.02387 0.0221 0.0408 1.0000
10.250 0.9120 0.03353 0.02547 0.0215 0.0399 1.0000
10.500 0.9463 0.03547 0.02762 0.0204 0.0397 1.0000
10.750 0.9781 0.03796 0.03040 0.0196 0.0399 1.0000
11.000 1.0040 0.04088 0.03362 0.0193 0.0405 1.0000
11.250 1.0289 0.04462 0.03763 0.0189 0.0416 1.0000
11.500 1.0585 0.04786 0.04107 0.0179 0.0434 1.0000
11.750 0.9794 0.04582 0.04004 0.0279 0.0498 1.0000
12.000 0.9309 0.06902 0.06462 0.0377 0.0905 1.0000
12.250 0.8955 0.07155 0.06735 0.0412 0.0889 1.0000
12.500 0.8666 0.07552 0.07147 0.0428 0.0886 1.0000
12.750 0.8347 0.07996 0.07606 0.0434 0.0877 1.0000
13.000 0.7987 0.08583 0.08206 0.0426 0.0876 1.0000
13.250 0.7553 0.09386 0.09020 0.0395 0.0880 1.0000
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Polar data table (+)
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