NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.25 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9660-il-1000000-n5.txt Download as CSV file: xf-npl9660-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.1298 0.06623 0.06372 -0.0175 1.0000 0.0097
-15.000 -1.1598 0.05660 0.05386 -0.0246 1.0000 0.0097
-14.750 -1.1782 0.05017 0.04724 -0.0286 1.0000 0.0097
-14.500 -1.1908 0.04537 0.04225 -0.0307 1.0000 0.0097
-14.250 -1.1994 0.04160 0.03832 -0.0316 1.0000 0.0097
-14.000 -1.2046 0.03858 0.03513 -0.0314 1.0000 0.0097
-13.750 -1.2070 0.03608 0.03248 -0.0305 1.0000 0.0097
-13.500 -1.2068 0.03396 0.03021 -0.0292 1.0000 0.0097
-13.250 -1.2042 0.03212 0.02823 -0.0276 1.0000 0.0097
-13.000 -1.1993 0.03053 0.02650 -0.0258 1.0000 0.0097
-12.750 -1.1908 0.02908 0.02491 -0.0241 1.0000 0.0097
-12.500 -1.1781 0.02770 0.02340 -0.0230 1.0000 0.0097
-12.250 -1.1632 0.02643 0.02201 -0.0220 1.0000 0.0097
-11.750 -1.1281 0.02415 0.01948 -0.0204 0.9915 0.0097
-11.500 -1.1070 0.02309 0.01831 -0.0202 0.9879 0.0098
-11.250 -1.0850 0.02211 0.01722 -0.0200 0.9847 0.0098
-11.000 -1.0626 0.02120 0.01620 -0.0198 0.9821 0.0099
-10.750 -1.0412 0.02038 0.01529 -0.0192 0.9793 0.0099
-10.500 -1.0196 0.01963 0.01445 -0.0185 0.9765 0.0099
-10.250 -0.9976 0.01895 0.01368 -0.0179 0.9740 0.0099
-9.750 -0.9530 0.01769 0.01227 -0.0165 0.9684 0.0099
-9.500 -0.9307 0.01712 0.01163 -0.0157 0.9652 0.0099
-9.250 -0.9084 0.01659 0.01103 -0.0149 0.9622 0.0099
-9.000 -0.8858 0.01610 0.01048 -0.0141 0.9595 0.0099
-8.750 -0.8615 0.01557 0.00990 -0.0137 0.9567 0.0099
-8.500 -0.8372 0.01508 0.00937 -0.0131 0.9537 0.0099
-8.250 -0.8135 0.01463 0.00886 -0.0125 0.9505 0.0099
-8.000 -0.7895 0.01420 0.00839 -0.0118 0.9473 0.0099
-7.750 -0.7640 0.01374 0.00790 -0.0115 0.9431 0.0099
-7.500 -0.7390 0.01333 0.00744 -0.0110 0.9392 0.0099
-7.250 -0.7142 0.01293 0.00702 -0.0105 0.9360 0.0099
-7.000 -0.6881 0.01255 0.00660 -0.0102 0.9321 0.0099
-6.750 -0.6622 0.01218 0.00621 -0.0099 0.9278 0.0099
-6.500 -0.6369 0.01184 0.00583 -0.0094 0.9235 0.0099
-6.250 -0.6115 0.01151 0.00548 -0.0089 0.9192 0.0100
-6.000 -0.5848 0.01120 0.00515 -0.0087 0.9132 0.0100
-5.750 -0.5591 0.01091 0.00482 -0.0082 0.9068 0.0100
-5.500 -0.5325 0.01064 0.00452 -0.0079 0.9008 0.0101
-5.250 -0.5056 0.01038 0.00424 -0.0077 0.8926 0.0101
-5.000 -0.4790 0.01014 0.00396 -0.0074 0.8850 0.0101
-4.750 -0.4515 0.00991 0.00370 -0.0073 0.8757 0.0102
-4.500 -0.4244 0.00971 0.00346 -0.0071 0.8650 0.0102
-4.250 -0.3973 0.00952 0.00322 -0.0069 0.8511 0.0103
-4.000 -0.3699 0.00935 0.00299 -0.0068 0.8356 0.0104
-3.750 -0.3425 0.00921 0.00278 -0.0066 0.8169 0.0105
-3.500 -0.3148 0.00911 0.00258 -0.0065 0.7918 0.0106
-3.250 -0.2873 0.00905 0.00240 -0.0064 0.7566 0.0107
-3.000 -0.2592 0.00900 0.00224 -0.0064 0.7277 0.0110
-2.750 -0.2309 0.00894 0.00211 -0.0065 0.7074 0.0112
-2.500 -0.2024 0.00886 0.00199 -0.0067 0.6902 0.0117
-2.250 -0.1739 0.00879 0.00188 -0.0068 0.6709 0.0124
-2.000 -0.1453 0.00871 0.00177 -0.0070 0.6516 0.0173
-1.750 -0.1166 0.00868 0.00169 -0.0071 0.6326 0.0186
-1.500 -0.0880 0.00863 0.00161 -0.0073 0.6129 0.0217
-1.250 -0.0593 0.00860 0.00156 -0.0075 0.5930 0.0287
-0.750 -0.0017 0.00858 0.00146 -0.0079 0.5579 0.0339
-0.500 0.0271 0.00857 0.00142 -0.0082 0.5389 0.0380
-0.250 0.0557 0.00857 0.00139 -0.0084 0.5169 0.0456
0.000 0.0844 0.00860 0.00137 -0.0086 0.4916 0.0543
0.250 0.1129 0.00863 0.00135 -0.0088 0.4616 0.0716
0.500 0.1388 0.00740 0.00116 -0.0094 0.4397 0.4299
0.750 0.1669 0.00714 0.00116 -0.0097 0.4220 0.5222
1.000 0.1952 0.00698 0.00117 -0.0100 0.4065 0.5916
1.250 0.2235 0.00685 0.00120 -0.0102 0.3893 0.6547
1.500 0.2517 0.00680 0.00124 -0.0104 0.3668 0.7051
1.750 0.2797 0.00676 0.00131 -0.0104 0.3480 0.7531
2.000 0.3064 0.00671 0.00142 -0.0101 0.3291 0.8177
2.250 0.3320 0.00680 0.00158 -0.0095 0.3068 0.8622
2.500 0.3593 0.00698 0.00169 -0.0093 0.2834 0.8763
2.750 0.3874 0.00718 0.00180 -0.0094 0.2584 0.8846
3.000 0.4149 0.00736 0.00192 -0.0094 0.2418 0.8909
3.250 0.4424 0.00758 0.00206 -0.0093 0.2180 0.8973
3.500 0.4703 0.00785 0.00220 -0.0095 0.1921 0.9033
3.750 0.4970 0.00806 0.00236 -0.0092 0.1739 0.9080
4.000 0.5241 0.00826 0.00250 -0.0091 0.1618 0.9129
4.250 0.5518 0.00847 0.00266 -0.0091 0.1489 0.9176
4.500 0.5792 0.00868 0.00282 -0.0091 0.1379 0.9215
4.750 0.6054 0.00890 0.00300 -0.0088 0.1267 0.9249
5.000 0.6321 0.00915 0.00318 -0.0086 0.1143 0.9286
5.250 0.6591 0.00941 0.00339 -0.0085 0.1033 0.9322
5.500 0.6867 0.00964 0.00358 -0.0086 0.0959 0.9354
6.000 0.7391 0.01008 0.00396 -0.0080 0.0759 0.9421
6.250 0.7656 0.01038 0.00420 -0.0079 0.0702 0.9462
6.500 0.7920 0.01069 0.00447 -0.0078 0.0593 0.9489
6.750 0.8169 0.01103 0.00475 -0.0074 0.0468 0.9513
7.000 0.8417 0.01141 0.00507 -0.0070 0.0356 0.9542
7.250 0.8671 0.01175 0.00538 -0.0067 0.0290 0.9570
7.500 0.8930 0.01209 0.00570 -0.0065 0.0251 0.9595
7.750 0.9173 0.01236 0.00596 -0.0060 0.0225 0.9620
8.000 0.9415 0.01262 0.00624 -0.0054 0.0208 0.9650
8.250 0.9661 0.01290 0.00654 -0.0050 0.0196 0.9679
8.500 0.9911 0.01323 0.00687 -0.0047 0.0184 0.9701
8.750 1.0164 0.01354 0.00721 -0.0044 0.0177 0.9719
9.000 1.0414 0.01384 0.00753 -0.0042 0.0170 0.9741
9.250 1.0661 0.01417 0.00789 -0.0038 0.0163 0.9766
9.500 1.0906 0.01455 0.00829 -0.0035 0.0157 0.9790
9.750 1.1150 0.01499 0.00875 -0.0033 0.0149 0.9812
10.000 1.1406 0.01538 0.00918 -0.0033 0.0145 0.9833
10.250 1.1668 0.01579 0.00963 -0.0034 0.0141 0.9857
10.500 1.1930 0.01623 0.01011 -0.0036 0.0135 0.9884
10.750 1.2186 0.01670 0.01063 -0.0038 0.0130 0.9918
11.250 1.2646 0.01781 0.01179 -0.0031 0.0121 1.0000
11.500 1.2866 0.01839 0.01243 -0.0027 0.0118 1.0000
11.750 1.3086 0.01893 0.01302 -0.0022 0.0116 1.0000
12.000 1.3299 0.01952 0.01366 -0.0017 0.0113 1.0000
12.250 1.3503 0.02013 0.01433 -0.0011 0.0111 1.0000
12.500 1.3697 0.02079 0.01504 -0.0003 0.0109 1.0000
12.750 1.3881 0.02148 0.01579 0.0005 0.0106 1.0000
13.000 1.4040 0.02220 0.01657 0.0017 0.0104 1.0000
13.250 1.4178 0.02299 0.01742 0.0031 0.0103 1.0000
13.500 1.4308 0.02386 0.01835 0.0045 0.0101 1.0000
13.750 1.4428 0.02483 0.01938 0.0058 0.0100 1.0000
14.000 1.4535 0.02591 0.02054 0.0071 0.0099 1.0000
14.250 1.4628 0.02714 0.02184 0.0084 0.0097 1.0000
14.500 1.4703 0.02857 0.02335 0.0096 0.0096 1.0000
14.750 1.4756 0.03026 0.02513 0.0106 0.0095 1.0000
15.000 1.4799 0.03215 0.02712 0.0114 0.0094 1.0000
15.250 1.4845 0.03414 0.02920 0.0118 0.0093 1.0000
15.500 1.4881 0.03636 0.03153 0.0119 0.0093 1.0000
15.750 1.4898 0.03896 0.03423 0.0117 0.0092 1.0000
16.000 1.4891 0.04197 0.03736 0.0111 0.0092 1.0000
16.250 1.4865 0.04540 0.04091 0.0101 0.0091 1.0000
16.500 1.4814 0.04932 0.04495 0.0087 0.0091 1.0000
16.750 1.4736 0.05378 0.04954 0.0069 0.0091 1.0000
17.000 1.4626 0.05885 0.05474 0.0047 0.0090 1.0000
17.250 1.4485 0.06450 0.06053 0.0021 0.0090 1.0000
17.500 1.4312 0.07085 0.06702 -0.0008 0.0090 1.0000
17.750 1.4103 0.07789 0.07420 -0.0042 0.0090 1.0000
18.000 1.3866 0.08561 0.08207 -0.0079 0.0090 1.0000
18.250 1.3598 0.09405 0.09065 -0.0121 0.0090 1.0000
18.500 1.3321 0.10285 0.09959 -0.0164 0.0090 1.0000
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Polar data table (+)
Polar graphs
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