NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.68 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9615-il-1000000.txt Download as CSV file: xf-npl9615-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9615 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9608 0.05690 0.05461 -0.0432 1.0000 0.0141
-13.500 -1.0173 0.04611 0.04345 -0.0488 1.0000 0.0139
-13.250 -1.0473 0.04066 0.03770 -0.0487 1.0000 0.0138
-13.000 -1.0674 0.03689 0.03368 -0.0465 1.0000 0.0138
-12.750 -1.0803 0.03409 0.03065 -0.0433 1.0000 0.0138
-12.500 -1.0868 0.03204 0.02840 -0.0397 1.0000 0.0138
-12.250 -1.0876 0.03026 0.02644 -0.0363 1.0000 0.0138
-12.000 -1.0831 0.02860 0.02461 -0.0336 1.0000 0.0139
-11.750 -1.0753 0.02718 0.02304 -0.0311 1.0000 0.0139
-11.500 -1.0657 0.02587 0.02157 -0.0286 1.0000 0.0140
-11.250 -1.0538 0.02474 0.02031 -0.0264 1.0000 0.0141
-11.000 -1.0410 0.02363 0.01906 -0.0243 1.0000 0.0142
-10.750 -1.0273 0.02257 0.01787 -0.0222 1.0000 0.0142
-10.500 -1.0130 0.02154 0.01672 -0.0201 1.0000 0.0143
-10.250 -0.9984 0.02054 0.01560 -0.0180 1.0000 0.0143
-10.000 -0.9828 0.01964 0.01459 -0.0160 1.0000 0.0143
-9.750 -0.9663 0.01886 0.01372 -0.0141 1.0000 0.0143
-9.500 -0.9498 0.01810 0.01287 -0.0122 1.0000 0.0143
-9.250 -0.9340 0.01731 0.01199 -0.0101 1.0000 0.0143
-9.000 -0.9183 0.01659 0.01120 -0.0079 1.0000 0.0143
-8.750 -0.9027 0.01595 0.01049 -0.0056 1.0000 0.0142
-8.500 -0.8774 0.01526 0.00972 -0.0054 0.9992 0.0142
-8.250 -0.8464 0.01458 0.00897 -0.0064 0.9976 0.0142
-8.000 -0.8147 0.01395 0.00829 -0.0075 0.9955 0.0141
-7.750 -0.7830 0.01339 0.00768 -0.0086 0.9932 0.0141
-7.500 -0.7512 0.01287 0.00712 -0.0097 0.9910 0.0141
-7.250 -0.7190 0.01240 0.00661 -0.0108 0.9891 0.0141
-7.000 -0.6918 0.01197 0.00615 -0.0107 0.9847 0.0141
-6.750 -0.6616 0.01157 0.00571 -0.0113 0.9804 0.0141
-6.500 -0.6298 0.01119 0.00531 -0.0123 0.9765 0.0141
-6.250 -0.5967 0.01083 0.00493 -0.0135 0.9734 0.0141
-6.000 -0.5668 0.01052 0.00459 -0.0140 0.9682 0.0141
-5.750 -0.5330 0.01021 0.00427 -0.0153 0.9642 0.0142
-5.500 -0.4981 0.00992 0.00396 -0.0169 0.9604 0.0143
-5.250 -0.4626 0.00965 0.00367 -0.0186 0.9567 0.0144
-5.000 -0.4322 0.00942 0.00343 -0.0191 0.9493 0.0146
-4.750 -0.3993 0.00919 0.00319 -0.0202 0.9417 0.0152
-4.500 -0.3701 0.00900 0.00298 -0.0205 0.9308 0.0161
-4.250 -0.3410 0.00883 0.00278 -0.0206 0.9176 0.0173
-4.000 -0.3133 0.00869 0.00259 -0.0205 0.9022 0.0186
-3.750 -0.2865 0.00857 0.00243 -0.0201 0.8868 0.0204
-3.500 -0.2602 0.00845 0.00229 -0.0197 0.8728 0.0237
-3.250 -0.2338 0.00835 0.00218 -0.0193 0.8593 0.0276
-3.000 -0.2075 0.00826 0.00207 -0.0189 0.8424 0.0298
-2.750 -0.1822 0.00822 0.00195 -0.0182 0.8085 0.0319
-2.500 -0.1577 0.00822 0.00183 -0.0173 0.7834 0.0335
-2.250 -0.1322 0.00821 0.00175 -0.0167 0.7658 0.0357
-2.000 -0.1063 0.00818 0.00167 -0.0162 0.7490 0.0379
-1.750 -0.0802 0.00814 0.00160 -0.0157 0.7314 0.0400
-1.500 -0.0541 0.00809 0.00153 -0.0153 0.7138 0.0431
-1.250 -0.0283 0.00806 0.00146 -0.0148 0.6944 0.0476
-1.000 -0.0026 0.00803 0.00140 -0.0142 0.6760 0.0549
-0.750 0.0229 0.00797 0.00135 -0.0137 0.6562 0.0694
-0.500 0.0448 0.00763 0.00124 -0.0125 0.6305 0.1693
-0.250 0.0568 0.00651 0.00104 -0.0098 0.6051 0.4695
0.000 0.0779 0.00625 0.00101 -0.0084 0.5809 0.5588
0.250 0.0995 0.00604 0.00101 -0.0070 0.5619 0.6346
0.500 0.1209 0.00588 0.00103 -0.0056 0.5440 0.7029
0.750 0.1426 0.00576 0.00104 -0.0041 0.5252 0.7642
1.000 0.1622 0.00560 0.00114 -0.0020 0.5072 0.8414
1.250 0.1872 0.00563 0.00120 -0.0012 0.4903 0.8733
1.500 0.2137 0.00568 0.00127 -0.0007 0.4727 0.9005
1.750 0.2419 0.00577 0.00135 -0.0006 0.4560 0.9181
2.000 0.2696 0.00588 0.00141 -0.0004 0.4397 0.9306
2.250 0.3010 0.00601 0.00150 -0.0011 0.4219 0.9419
2.500 0.3303 0.00615 0.00158 -0.0014 0.4034 0.9504
2.750 0.3655 0.00632 0.00168 -0.0030 0.3811 0.9546
3.000 0.3989 0.00655 0.00179 -0.0043 0.3540 0.9587
3.250 0.4293 0.00678 0.00191 -0.0049 0.3237 0.9636
3.500 0.4577 0.00710 0.00206 -0.0051 0.2851 0.9686
3.750 0.4925 0.00744 0.00223 -0.0068 0.2468 0.9706
4.500 0.5900 0.00838 0.00278 -0.0104 0.1666 0.9790
4.750 0.6205 0.00867 0.00297 -0.0111 0.1474 0.9825
5.000 0.6483 0.00894 0.00317 -0.0112 0.1325 0.9866
5.250 0.6811 0.00917 0.00335 -0.0124 0.1218 0.9884
5.500 0.7153 0.00938 0.00351 -0.0140 0.1147 0.9900
5.750 0.7489 0.00958 0.00369 -0.0154 0.1086 0.9918
6.000 0.7825 0.00980 0.00388 -0.0169 0.1027 0.9938
6.250 0.8162 0.01003 0.00409 -0.0183 0.0963 0.9959
6.500 0.8499 0.01022 0.00427 -0.0198 0.0900 0.9977
6.750 0.8824 0.01047 0.00446 -0.0210 0.0805 0.9991
7.000 0.9120 0.01077 0.00472 -0.0216 0.0679 1.0000
7.250 0.9300 0.01116 0.00505 -0.0198 0.0546 1.0000
7.500 0.9470 0.01163 0.00543 -0.0179 0.0401 1.0000
7.750 0.9647 0.01206 0.00581 -0.0161 0.0324 1.0000
8.000 0.9832 0.01244 0.00617 -0.0143 0.0287 1.0000
8.250 1.0024 0.01280 0.00653 -0.0128 0.0265 1.0000
8.500 1.0214 0.01320 0.00693 -0.0112 0.0247 1.0000
8.750 1.0413 0.01354 0.00729 -0.0097 0.0232 1.0000
9.000 1.0598 0.01398 0.00774 -0.0081 0.0219 1.0000
9.250 1.0796 0.01433 0.00813 -0.0067 0.0208 1.0000
9.500 1.0979 0.01481 0.00862 -0.0051 0.0197 1.0000
9.750 1.1164 0.01528 0.00913 -0.0035 0.0188 1.0000
10.000 1.1352 0.01573 0.00961 -0.0020 0.0179 1.0000
10.250 1.1523 0.01629 0.01020 -0.0002 0.0172 1.0000
10.500 1.1679 0.01695 0.01091 0.0017 0.0166 1.0000
10.750 1.1854 0.01745 0.01146 0.0034 0.0162 1.0000
11.000 1.2018 0.01800 0.01206 0.0052 0.0158 1.0000
11.250 1.2174 0.01858 0.01269 0.0070 0.0154 1.0000
11.500 1.2321 0.01920 0.01336 0.0090 0.0151 1.0000
11.750 1.2451 0.01992 0.01412 0.0112 0.0149 1.0000
12.000 1.2535 0.02081 0.01506 0.0140 0.0146 1.0000
12.250 1.2566 0.02187 0.01620 0.0175 0.0144 1.0000
12.500 1.2676 0.02260 0.01700 0.0197 0.0143 1.0000
12.750 1.2776 0.02345 0.01792 0.0218 0.0141 1.0000
13.000 1.2865 0.02441 0.01896 0.0238 0.0140 1.0000
13.250 1.2946 0.02550 0.02013 0.0257 0.0139 1.0000
13.500 1.3016 0.02673 0.02144 0.0273 0.0137 1.0000
13.750 1.3077 0.02813 0.02292 0.0288 0.0136 1.0000
14.000 1.3129 0.02969 0.02457 0.0301 0.0134 1.0000
14.250 1.3173 0.03143 0.02640 0.0310 0.0133 1.0000
14.500 1.3214 0.03335 0.02841 0.0316 0.0132 1.0000
14.750 1.3247 0.03548 0.03062 0.0319 0.0130 1.0000
15.000 1.3272 0.03781 0.03304 0.0319 0.0129 1.0000
15.250 1.3281 0.04047 0.03578 0.0315 0.0128 1.0000
15.500 1.3274 0.04341 0.03881 0.0310 0.0127 1.0000
15.750 1.3247 0.04675 0.04225 0.0301 0.0126 1.0000
16.000 1.3200 0.05042 0.04601 0.0289 0.0125 1.0000
16.250 1.3134 0.05445 0.05013 0.0275 0.0124 1.0000
16.500 1.3052 0.05876 0.05454 0.0260 0.0124 1.0000
16.750 1.2953 0.06342 0.05930 0.0242 0.0123 1.0000
17.000 1.2845 0.06827 0.06425 0.0223 0.0123 1.0000
17.250 1.2728 0.07338 0.06946 0.0202 0.0122 1.0000
17.500 1.2606 0.07864 0.07482 0.0180 0.0122 1.0000
17.750 1.2477 0.08406 0.08035 0.0157 0.0121 1.0000
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