NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 50,000 Max Cl/Cd: 30.08 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9660-il-50000-n5.txt Download as CSV file: xf-npl9660-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9660 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5981 0.11745 0.10995 -0.0057 1.0000 0.0620
-10.750 -0.5932 0.11328 0.10578 -0.0068 1.0000 0.0614
-10.500 -0.5910 0.10873 0.10126 -0.0086 1.0000 0.0607
-10.250 -0.5910 0.10372 0.09628 -0.0110 1.0000 0.0599
-10.000 -0.5936 0.09806 0.09065 -0.0143 1.0000 0.0589
-9.750 -0.6010 0.09125 0.08386 -0.0194 1.0000 0.0577
-9.500 -0.6168 0.08428 0.07687 -0.0248 1.0000 0.0565
-9.250 -0.6388 0.07826 0.07078 -0.0280 1.0000 0.0554
-9.000 -0.6623 0.07293 0.06525 -0.0290 1.0000 0.0544
-8.500 -0.6867 0.06365 0.05521 -0.0283 1.0000 0.0531
-8.250 -0.6852 0.05990 0.05117 -0.0273 1.0000 0.0531
-8.000 -0.6796 0.05641 0.04744 -0.0263 1.0000 0.0534
-7.750 -0.6707 0.05324 0.04403 -0.0252 1.0000 0.0538
-7.500 -0.6603 0.05028 0.04084 -0.0240 1.0000 0.0544
-7.250 -0.6487 0.04749 0.03778 -0.0227 1.0000 0.0553
-7.000 -0.6359 0.04482 0.03481 -0.0213 1.0000 0.0564
-6.750 -0.6218 0.04224 0.03189 -0.0197 1.0000 0.0579
-6.500 -0.6068 0.03985 0.02903 -0.0180 1.0000 0.0606
-6.250 -0.5904 0.03774 0.02661 -0.0165 1.0000 0.0638
-6.000 -0.5725 0.03631 0.02512 -0.0153 1.0000 0.0686
-5.750 -0.5548 0.03469 0.02314 -0.0138 1.0000 0.0744
-5.500 -0.5350 0.03318 0.02163 -0.0127 1.0000 0.0791
-5.250 -0.5138 0.03175 0.01991 -0.0114 1.0000 0.0835
-5.000 -0.4918 0.03030 0.01833 -0.0103 1.0000 0.0880
-4.750 -0.4692 0.02903 0.01706 -0.0093 1.0000 0.0918
-4.500 -0.4464 0.02802 0.01595 -0.0082 1.0000 0.0965
-4.250 -0.4233 0.02716 0.01490 -0.0070 1.0000 0.1001
-4.000 -0.4016 0.02613 0.01396 -0.0058 1.0000 0.1041
-3.750 -0.3811 0.02536 0.01318 -0.0045 1.0000 0.1094
-3.500 -0.3610 0.02471 0.01242 -0.0031 1.0000 0.1142
-3.250 -0.3418 0.02400 0.01166 -0.0018 1.0000 0.1188
-3.000 -0.3228 0.02332 0.01100 -0.0006 1.0000 0.1263
-2.750 -0.3036 0.02269 0.01039 0.0005 1.0000 0.1371
-2.500 -0.2848 0.02200 0.00980 0.0016 1.0000 0.1543
-2.250 -0.2683 0.02036 0.00914 0.0024 1.0000 0.2778
-2.000 -0.2630 0.01888 0.00971 0.0081 1.0000 0.6832
-1.750 -0.2447 0.01930 0.01047 0.0127 1.0000 0.8156
-1.500 -0.2154 0.01996 0.01105 0.0144 0.9996 0.8968
-1.250 -0.0731 0.02079 0.01142 -0.0042 1.0000 0.9837
-1.000 -0.0267 0.02067 0.01113 -0.0091 1.0000 0.9972
-0.750 0.0148 0.02062 0.01093 -0.0133 0.9889 1.0000
-0.500 0.0618 0.02061 0.01079 -0.0183 0.9761 1.0000
-0.250 0.1106 0.02063 0.01070 -0.0233 0.9633 1.0000
0.000 0.1553 0.02063 0.01064 -0.0274 0.9474 1.0000
0.250 0.1904 0.02061 0.01058 -0.0295 0.9269 1.0000
0.500 0.2259 0.02056 0.01050 -0.0314 0.9079 1.0000
0.750 0.2579 0.02048 0.01041 -0.0324 0.8887 1.0000
1.000 0.2872 0.02039 0.01031 -0.0327 0.8693 1.0000
1.250 0.3125 0.02031 0.01023 -0.0321 0.8482 1.0000
1.500 0.3374 0.02022 0.01014 -0.0313 0.8269 1.0000
1.750 0.3616 0.02013 0.01004 -0.0303 0.8051 1.0000
2.000 0.3853 0.02004 0.00994 -0.0290 0.7834 1.0000
2.250 0.4087 0.01996 0.00982 -0.0275 0.7621 1.0000
2.500 0.4312 0.01990 0.00974 -0.0259 0.7396 1.0000
2.750 0.4524 0.01991 0.00972 -0.0240 0.7148 1.0000
3.000 0.4738 0.01994 0.00969 -0.0222 0.6901 1.0000
3.250 0.4950 0.01999 0.00967 -0.0203 0.6650 1.0000
3.500 0.5151 0.02015 0.00982 -0.0184 0.6380 1.0000
3.750 0.5359 0.02029 0.00989 -0.0166 0.6124 1.0000
4.000 0.5563 0.02051 0.01008 -0.0149 0.5854 1.0000
4.250 0.5768 0.02074 0.01026 -0.0131 0.5581 1.0000
4.500 0.5970 0.02102 0.01052 -0.0115 0.5293 1.0000
4.750 0.6170 0.02133 0.01075 -0.0097 0.4998 1.0000
5.000 0.6367 0.02170 0.01108 -0.0081 0.4679 1.0000
5.250 0.6564 0.02211 0.01144 -0.0066 0.4365 1.0000
5.500 0.6761 0.02259 0.01185 -0.0050 0.4054 1.0000
5.750 0.6957 0.02315 0.01235 -0.0036 0.3734 1.0000
6.000 0.7154 0.02378 0.01290 -0.0023 0.3432 1.0000
6.250 0.7349 0.02449 0.01349 -0.0010 0.3166 1.0000
6.500 0.7551 0.02527 0.01425 0.0000 0.2919 1.0000
6.750 0.7754 0.02610 0.01505 0.0011 0.2702 1.0000
7.000 0.7953 0.02698 0.01587 0.0021 0.2509 1.0000
7.250 0.8154 0.02793 0.01681 0.0031 0.2330 1.0000
7.500 0.8351 0.02891 0.01780 0.0040 0.2158 1.0000
7.750 0.8540 0.02992 0.01884 0.0050 0.1988 1.0000
8.000 0.8716 0.03096 0.01989 0.0061 0.1817 1.0000
8.250 0.8880 0.03205 0.02098 0.0072 0.1651 1.0000
8.500 0.9037 0.03322 0.02224 0.0084 0.1485 1.0000
8.750 0.9185 0.03449 0.02362 0.0096 0.1331 1.0000
9.000 0.9324 0.03581 0.02498 0.0108 0.1197 1.0000
9.250 0.9457 0.03724 0.02645 0.0120 0.1081 1.0000
9.500 0.9587 0.03878 0.02806 0.0132 0.0984 1.0000
9.750 0.9717 0.04049 0.02990 0.0144 0.0903 1.0000
10.000 0.9848 0.04226 0.03177 0.0156 0.0842 1.0000
10.250 0.9968 0.04419 0.03386 0.0167 0.0790 1.0000
10.500 1.0066 0.04622 0.03607 0.0179 0.0745 1.0000
10.750 1.0157 0.04808 0.03800 0.0191 0.0712 1.0000
11.000 1.0212 0.05053 0.04071 0.0205 0.0683 1.0000
11.250 1.0259 0.05322 0.04360 0.0216 0.0663 1.0000
11.500 1.0241 0.05647 0.04718 0.0227 0.0647 1.0000
11.750 1.0233 0.05945 0.05035 0.0234 0.0632 1.0000
12.000 1.0213 0.06256 0.05359 0.0237 0.0619 1.0000
12.250 1.0035 0.06751 0.05889 0.0230 0.0613 1.0000
12.500 0.9820 0.07334 0.06504 0.0210 0.0609 1.0000
12.750 0.9560 0.08050 0.07245 0.0173 0.0610 1.0000
13.000 0.9251 0.08946 0.08163 0.0118 0.0614 1.0000
13.250 0.8912 0.10029 0.09262 0.0048 0.0619 1.0000
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Polar data table (+)
Polar graphs
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