NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 500,000 Max Cl/Cd: 66.22 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9660-il-500000-n5.txt Download as CSV file: xf-npl9660-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -1.0738 0.05580 0.05260 -0.0274 1.0000 0.0117
-13.750 -1.0996 0.04883 0.04534 -0.0311 1.0000 0.0117
-13.500 -1.1159 0.04407 0.04033 -0.0322 1.0000 0.0117
-13.250 -1.1259 0.04052 0.03654 -0.0319 1.0000 0.0117
-13.000 -1.1310 0.03772 0.03352 -0.0307 1.0000 0.0117
-12.750 -1.1323 0.03538 0.03098 -0.0291 1.0000 0.0117
-12.500 -1.1299 0.03343 0.02884 -0.0273 1.0000 0.0117
-12.250 -1.1227 0.03174 0.02698 -0.0257 1.0000 0.0118
-12.000 -1.1113 0.03016 0.02523 -0.0245 1.0000 0.0118
-11.750 -1.0976 0.02870 0.02360 -0.0235 1.0000 0.0119
-11.500 -1.0821 0.02733 0.02208 -0.0226 1.0000 0.0120
-11.250 -1.0651 0.02605 0.02064 -0.0217 1.0000 0.0120
-11.000 -1.0468 0.02487 0.01932 -0.0209 1.0000 0.0120
-10.750 -1.0274 0.02378 0.01810 -0.0202 1.0000 0.0120
-10.500 -1.0070 0.02278 0.01697 -0.0196 1.0000 0.0120
-10.250 -0.9860 0.02186 0.01593 -0.0190 1.0000 0.0120
-10.000 -0.9644 0.02100 0.01497 -0.0185 1.0000 0.0120
-9.750 -0.9423 0.02020 0.01409 -0.0179 1.0000 0.0120
-9.500 -0.9201 0.01946 0.01326 -0.0173 1.0000 0.0121
-9.250 -0.8979 0.01878 0.01249 -0.0167 1.0000 0.0121
-9.000 -0.8760 0.01815 0.01179 -0.0160 1.0000 0.0121
-8.750 -0.8499 0.01752 0.01109 -0.0161 0.9950 0.0121
-8.500 -0.8199 0.01691 0.01040 -0.0169 0.9904 0.0122
-8.250 -0.7898 0.01633 0.00976 -0.0178 0.9874 0.0122
-8.000 -0.7594 0.01580 0.00917 -0.0187 0.9848 0.0123
-7.750 -0.7292 0.01530 0.00861 -0.0195 0.9823 0.0124
-7.500 -0.7021 0.01488 0.00814 -0.0195 0.9787 0.0124
-7.250 -0.6753 0.01450 0.00771 -0.0195 0.9741 0.0125
-7.000 -0.6500 0.01418 0.00735 -0.0191 0.9689 0.0126
-6.750 -0.6260 0.01388 0.00700 -0.0184 0.9635 0.0127
-6.500 -0.6019 0.01359 0.00668 -0.0176 0.9593 0.0128
-6.250 -0.5772 0.01326 0.00634 -0.0171 0.9542 0.0130
-6.000 -0.5531 0.01298 0.00603 -0.0163 0.9493 0.0133
-5.750 -0.5276 0.01266 0.00570 -0.0159 0.9441 0.0138
-5.500 -0.5027 0.01235 0.00539 -0.0153 0.9384 0.0145
-5.250 -0.4777 0.01206 0.00509 -0.0147 0.9331 0.0160
-5.000 -0.4519 0.01179 0.00480 -0.0142 0.9270 0.0181
-4.750 -0.4273 0.01153 0.00454 -0.0134 0.9217 0.0200
-4.500 -0.4010 0.01129 0.00432 -0.0131 0.9157 0.0228
-4.250 -0.3749 0.01107 0.00410 -0.0127 0.9094 0.0252
-4.000 -0.3496 0.01087 0.00388 -0.0120 0.9040 0.0271
-3.750 -0.3221 0.01068 0.00368 -0.0119 0.8961 0.0287
-3.500 -0.2961 0.01050 0.00347 -0.0114 0.8881 0.0299
-3.250 -0.2691 0.01032 0.00328 -0.0111 0.8782 0.0313
-3.000 -0.2428 0.01016 0.00309 -0.0107 0.8668 0.0327
-2.750 -0.2163 0.01001 0.00290 -0.0102 0.8519 0.0339
-2.500 -0.1898 0.00986 0.00272 -0.0098 0.8356 0.0356
-2.250 -0.1631 0.00974 0.00255 -0.0094 0.8170 0.0378
-2.000 -0.1360 0.00964 0.00241 -0.0091 0.7956 0.0411
-1.750 -0.1086 0.00956 0.00227 -0.0089 0.7711 0.0450
-1.500 -0.0812 0.00950 0.00215 -0.0088 0.7468 0.0496
-1.250 -0.0535 0.00947 0.00204 -0.0087 0.7244 0.0555
-1.000 -0.0256 0.00941 0.00194 -0.0087 0.7024 0.0660
-0.750 0.0024 0.00933 0.00186 -0.0087 0.6823 0.0853
-0.500 0.0260 0.00786 0.00156 -0.0090 0.6614 0.4400
-0.250 0.0534 0.00760 0.00151 -0.0091 0.6380 0.5216
0.000 0.0808 0.00739 0.00148 -0.0091 0.6153 0.5936
0.250 0.1082 0.00726 0.00148 -0.0091 0.5924 0.6548
0.500 0.1352 0.00715 0.00150 -0.0089 0.5686 0.7128
0.750 0.1615 0.00710 0.00156 -0.0084 0.5418 0.7662
1.000 0.1866 0.00714 0.00168 -0.0076 0.5150 0.8194
1.250 0.2099 0.00726 0.00186 -0.0062 0.4933 0.8623
1.500 0.2353 0.00742 0.00198 -0.0054 0.4742 0.8855
1.750 0.2613 0.00757 0.00208 -0.0049 0.4571 0.8944
2.000 0.2891 0.00772 0.00215 -0.0048 0.4390 0.9023
2.250 0.3155 0.00787 0.00224 -0.0044 0.4218 0.9078
2.500 0.3420 0.00803 0.00234 -0.0040 0.4031 0.9138
2.750 0.3697 0.00821 0.00243 -0.0040 0.3817 0.9201
3.000 0.3951 0.00840 0.00256 -0.0034 0.3596 0.9245
3.250 0.4211 0.00862 0.00268 -0.0030 0.3370 0.9296
3.500 0.4481 0.00885 0.00282 -0.0029 0.3113 0.9349
3.750 0.4733 0.00911 0.00297 -0.0024 0.2827 0.9394
4.000 0.4990 0.00941 0.00313 -0.0021 0.2527 0.9447
4.250 0.5252 0.00969 0.00331 -0.0018 0.2307 0.9493
4.500 0.5502 0.00993 0.00346 -0.0013 0.2070 0.9537
4.750 0.5759 0.01018 0.00363 -0.0010 0.1879 0.9583
5.000 0.6010 0.01039 0.00378 -0.0005 0.1721 0.9625
5.250 0.6260 0.01058 0.00392 0.0000 0.1592 0.9678
5.500 0.6517 0.01080 0.00409 0.0003 0.1449 0.9726
5.750 0.6790 0.01108 0.00428 0.0002 0.1288 0.9761
6.000 0.7070 0.01133 0.00449 -0.0001 0.1175 0.9792
6.250 0.7355 0.01159 0.00472 -0.0005 0.1090 0.9825
6.500 0.7669 0.01188 0.00499 -0.0015 0.1001 0.9849
6.750 0.7983 0.01220 0.00528 -0.0026 0.0897 0.9874
7.000 0.8297 0.01258 0.00558 -0.0037 0.0739 0.9903
7.250 0.8608 0.01300 0.00596 -0.0048 0.0619 0.9943
7.500 0.8897 0.01347 0.00638 -0.0055 0.0496 1.0000
7.750 0.9118 0.01395 0.00680 -0.0048 0.0396 1.0000
8.000 0.9349 0.01442 0.00725 -0.0043 0.0328 1.0000
8.250 0.9585 0.01489 0.00772 -0.0039 0.0286 1.0000
8.500 0.9822 0.01538 0.00821 -0.0035 0.0258 1.0000
8.750 1.0065 0.01583 0.00868 -0.0032 0.0240 1.0000
9.000 1.0304 0.01632 0.00921 -0.0029 0.0224 1.0000
9.250 1.0540 0.01686 0.00977 -0.0026 0.0213 1.0000
9.500 1.0777 0.01736 0.01032 -0.0023 0.0204 1.0000
9.750 1.1009 0.01790 0.01092 -0.0019 0.0195 1.0000
10.000 1.1233 0.01852 0.01157 -0.0015 0.0187 1.0000
10.250 1.1446 0.01922 0.01232 -0.0009 0.0179 1.0000
10.500 1.1664 0.01983 0.01301 -0.0004 0.0174 1.0000
10.750 1.1872 0.02050 0.01375 0.0001 0.0168 1.0000
11.000 1.2072 0.02122 0.01453 0.0008 0.0163 1.0000
11.250 1.2261 0.02199 0.01537 0.0016 0.0158 1.0000
11.500 1.2433 0.02285 0.01629 0.0025 0.0154 1.0000
11.750 1.2574 0.02389 0.01739 0.0038 0.0150 1.0000
12.000 1.2687 0.02490 0.01848 0.0054 0.0147 1.0000
12.250 1.2810 0.02588 0.01956 0.0069 0.0145 1.0000
12.500 1.2920 0.02699 0.02077 0.0082 0.0142 1.0000
12.750 1.3017 0.02822 0.02210 0.0095 0.0140 1.0000
13.000 1.3101 0.02961 0.02359 0.0107 0.0138 1.0000
13.250 1.3172 0.03116 0.02525 0.0118 0.0136 1.0000
13.500 1.3232 0.03290 0.02710 0.0126 0.0134 1.0000
13.750 1.3280 0.03486 0.02917 0.0132 0.0132 1.0000
14.000 1.3315 0.03707 0.03149 0.0134 0.0131 1.0000
14.250 1.3338 0.03957 0.03410 0.0133 0.0129 1.0000
14.500 1.3347 0.04240 0.03704 0.0128 0.0128 1.0000
14.750 1.3340 0.04557 0.04033 0.0120 0.0127 1.0000
15.000 1.3317 0.04910 0.04399 0.0108 0.0126 1.0000
15.250 1.3275 0.05303 0.04803 0.0093 0.0125 1.0000
15.500 1.3216 0.05733 0.05247 0.0075 0.0125 1.0000
15.750 1.3136 0.06203 0.05729 0.0054 0.0124 1.0000
16.000 1.3039 0.06709 0.06248 0.0031 0.0123 1.0000
16.250 1.2927 0.07250 0.06802 0.0005 0.0123 1.0000
16.500 1.2803 0.07822 0.07386 -0.0022 0.0122 1.0000
16.750 1.2672 0.08421 0.07997 -0.0051 0.0122 1.0000
17.000 1.2533 0.09044 0.08631 -0.0081 0.0122 1.0000
17.250 1.2393 0.09680 0.09278 -0.0113 0.0121 1.0000
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