NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 500,000 Max Cl/Cd: 68.1 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9615-il-500000-n5.txt Download as CSV file: xf-npl9615-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9694 0.06386 0.06071 -0.0374 1.0000 0.0118
-14.000 -1.0044 0.05421 0.05079 -0.0442 1.0000 0.0118
-13.750 -1.0272 0.04809 0.04443 -0.0472 1.0000 0.0118
-13.500 -1.0435 0.04364 0.03976 -0.0480 1.0000 0.0118
-13.250 -1.0548 0.04026 0.03616 -0.0473 1.0000 0.0118
-13.000 -1.0623 0.03755 0.03324 -0.0458 1.0000 0.0118
-12.750 -1.0666 0.03532 0.03081 -0.0436 1.0000 0.0118
-12.500 -1.0681 0.03345 0.02876 -0.0409 1.0000 0.0118
-12.250 -1.0673 0.03183 0.02697 -0.0380 1.0000 0.0119
-12.000 -1.0630 0.03034 0.02531 -0.0353 1.0000 0.0119
-11.750 -1.0551 0.02891 0.02371 -0.0330 1.0000 0.0119
-11.500 -1.0453 0.02759 0.02224 -0.0308 1.0000 0.0119
-11.250 -1.0340 0.02639 0.02088 -0.0287 1.0000 0.0119
-11.000 -1.0214 0.02527 0.01964 -0.0266 1.0000 0.0119
-10.750 -1.0078 0.02424 0.01848 -0.0246 1.0000 0.0119
-10.500 -0.9933 0.02329 0.01741 -0.0226 1.0000 0.0119
-10.250 -0.9781 0.02240 0.01641 -0.0208 1.0000 0.0119
-10.000 -0.9621 0.02157 0.01548 -0.0189 1.0000 0.0119
-9.750 -0.9456 0.02080 0.01461 -0.0171 1.0000 0.0119
-9.500 -0.9286 0.02007 0.01381 -0.0153 1.0000 0.0119
-9.250 -0.9114 0.01939 0.01305 -0.0135 1.0000 0.0119
-9.000 -0.8940 0.01876 0.01234 -0.0118 1.0000 0.0119
-8.750 -0.8763 0.01817 0.01168 -0.0100 1.0000 0.0119
-8.500 -0.8587 0.01761 0.01106 -0.0082 1.0000 0.0119
-8.250 -0.8410 0.01709 0.01049 -0.0064 1.0000 0.0119
-8.000 -0.8186 0.01657 0.00990 -0.0055 0.9994 0.0119
-7.750 -0.7869 0.01600 0.00928 -0.0067 0.9969 0.0119
-7.500 -0.7540 0.01547 0.00869 -0.0080 0.9934 0.0119
-7.000 -0.6901 0.01449 0.00762 -0.0102 0.9830 0.0120
-6.750 -0.6590 0.01405 0.00713 -0.0111 0.9769 0.0121
-6.500 -0.6276 0.01364 0.00668 -0.0120 0.9714 0.0121
-6.250 -0.5969 0.01325 0.00626 -0.0127 0.9659 0.0122
-6.000 -0.5630 0.01286 0.00584 -0.0141 0.9614 0.0123
-5.750 -0.5282 0.01250 0.00544 -0.0157 0.9572 0.0124
-5.500 -0.4970 0.01217 0.00509 -0.0165 0.9502 0.0126
-5.250 -0.4635 0.01184 0.00474 -0.0178 0.9432 0.0128
-5.000 -0.4314 0.01153 0.00442 -0.0188 0.9349 0.0131
-4.750 -0.4002 0.01125 0.00411 -0.0196 0.9247 0.0135
-4.500 -0.3711 0.01098 0.00384 -0.0198 0.9138 0.0141
-4.250 -0.3418 0.01074 0.00358 -0.0201 0.9027 0.0165
-4.000 -0.3134 0.01056 0.00337 -0.0202 0.8912 0.0181
-3.750 -0.2862 0.01038 0.00317 -0.0200 0.8792 0.0213
-3.500 -0.2593 0.01023 0.00301 -0.0197 0.8663 0.0253
-3.250 -0.2329 0.01010 0.00286 -0.0193 0.8500 0.0289
-3.000 -0.2073 0.01001 0.00269 -0.0187 0.8153 0.0320
-2.750 -0.1827 0.00998 0.00250 -0.0178 0.7830 0.0339
-2.500 -0.1574 0.00994 0.00237 -0.0172 0.7638 0.0360
-2.250 -0.1317 0.00988 0.00226 -0.0166 0.7478 0.0381
-2.000 -0.1057 0.00982 0.00216 -0.0162 0.7326 0.0404
-1.500 -0.0542 0.00971 0.00197 -0.0151 0.6978 0.0467
-1.250 -0.0289 0.00968 0.00189 -0.0145 0.6761 0.0514
-1.000 -0.0038 0.00965 0.00181 -0.0139 0.6535 0.0581
-0.750 0.0210 0.00956 0.00174 -0.0132 0.6327 0.0791
-0.500 0.0311 0.00803 0.00145 -0.0104 0.6146 0.4484
-0.250 0.0509 0.00766 0.00140 -0.0087 0.5968 0.5554
0.000 0.0724 0.00745 0.00140 -0.0073 0.5807 0.6228
0.250 0.0949 0.00735 0.00141 -0.0061 0.5617 0.6736
0.500 0.1161 0.00726 0.00143 -0.0045 0.5367 0.7317
1.000 0.1611 0.00717 0.00161 -0.0016 0.4897 0.8489
1.250 0.1874 0.00727 0.00167 -0.0011 0.4674 0.8740
1.500 0.2151 0.00739 0.00174 -0.0010 0.4452 0.8916
1.750 0.2439 0.00751 0.00181 -0.0011 0.4264 0.9036
2.000 0.2734 0.00765 0.00189 -0.0014 0.4079 0.9127
2.250 0.3032 0.00779 0.00197 -0.0017 0.3892 0.9223
2.500 0.3328 0.00795 0.00206 -0.0021 0.3685 0.9307
2.750 0.3655 0.00814 0.00217 -0.0032 0.3466 0.9377
3.000 0.3947 0.00834 0.00228 -0.0035 0.3227 0.9454
3.250 0.4266 0.00859 0.00242 -0.0045 0.2959 0.9507
3.500 0.4606 0.00888 0.00259 -0.0060 0.2641 0.9546
3.750 0.4934 0.00918 0.00277 -0.0072 0.2397 0.9588
4.000 0.5247 0.00945 0.00295 -0.0081 0.2165 0.9634
4.250 0.5535 0.00974 0.00315 -0.0084 0.1952 0.9685
4.500 0.5864 0.01003 0.00335 -0.0097 0.1761 0.9715
4.750 0.6181 0.01031 0.00356 -0.0107 0.1598 0.9752
5.000 0.6488 0.01060 0.00378 -0.0115 0.1467 0.9796
5.250 0.6783 0.01088 0.00402 -0.0121 0.1341 0.9844
5.500 0.7082 0.01121 0.00426 -0.0128 0.1185 0.9884
5.750 0.7406 0.01150 0.00450 -0.0140 0.1074 0.9914
6.000 0.7716 0.01178 0.00474 -0.0150 0.0988 0.9942
6.250 0.8024 0.01209 0.00501 -0.0159 0.0916 0.9968
6.500 0.8333 0.01238 0.00526 -0.0168 0.0820 0.9988
6.750 0.8615 0.01265 0.00553 -0.0171 0.0727 1.0000
7.000 0.8814 0.01295 0.00583 -0.0157 0.0641 1.0000
7.250 0.9002 0.01335 0.00618 -0.0141 0.0538 1.0000
7.500 0.9187 0.01379 0.00656 -0.0124 0.0429 1.0000
7.750 0.9373 0.01424 0.00698 -0.0108 0.0351 1.0000
8.000 0.9562 0.01467 0.00739 -0.0093 0.0306 1.0000
8.250 0.9753 0.01509 0.00782 -0.0078 0.0277 1.0000
8.500 0.9945 0.01551 0.00825 -0.0063 0.0255 1.0000
8.750 1.0137 0.01593 0.00871 -0.0048 0.0239 1.0000
9.000 1.0326 0.01638 0.00918 -0.0033 0.0226 1.0000
9.250 1.0513 0.01685 0.00968 -0.0018 0.0215 1.0000
9.500 1.0698 0.01732 0.01020 -0.0003 0.0205 1.0000
9.750 1.0875 0.01785 0.01075 0.0013 0.0197 1.0000
10.000 1.1049 0.01838 0.01133 0.0029 0.0189 1.0000
10.250 1.1224 0.01891 0.01191 0.0045 0.0181 1.0000
10.500 1.1390 0.01949 0.01254 0.0062 0.0174 1.0000
10.750 1.1539 0.02018 0.01326 0.0080 0.0168 1.0000
11.000 1.1698 0.02079 0.01395 0.0098 0.0163 1.0000
11.250 1.1846 0.02145 0.01469 0.0116 0.0158 1.0000
11.500 1.1980 0.02216 0.01546 0.0135 0.0154 1.0000
11.750 1.2090 0.02290 0.01626 0.0159 0.0150 1.0000
12.000 1.2185 0.02374 0.01716 0.0183 0.0147 1.0000
12.250 1.2261 0.02474 0.01822 0.0207 0.0145 1.0000
12.500 1.2343 0.02577 0.01933 0.0228 0.0142 1.0000
12.750 1.2427 0.02685 0.02051 0.0246 0.0140 1.0000
13.000 1.2500 0.02808 0.02183 0.0263 0.0138 1.0000
13.250 1.2562 0.02946 0.02332 0.0278 0.0136 1.0000
13.500 1.2615 0.03101 0.02497 0.0290 0.0134 1.0000
13.750 1.2657 0.03276 0.02682 0.0300 0.0132 1.0000
14.000 1.2690 0.03476 0.02892 0.0306 0.0131 1.0000
14.250 1.2712 0.03700 0.03127 0.0309 0.0129 1.0000
14.500 1.2722 0.03951 0.03388 0.0309 0.0128 1.0000
14.750 1.2719 0.04232 0.03681 0.0305 0.0127 1.0000
15.000 1.2702 0.04546 0.04005 0.0298 0.0126 1.0000
15.250 1.2670 0.04893 0.04364 0.0287 0.0125 1.0000
15.500 1.2621 0.05276 0.04758 0.0274 0.0125 1.0000
15.750 1.2555 0.05695 0.05189 0.0258 0.0124 1.0000
16.000 1.2471 0.06148 0.05653 0.0239 0.0123 1.0000
16.250 1.2372 0.06635 0.06151 0.0218 0.0123 1.0000
16.500 1.2261 0.07150 0.06678 0.0195 0.0123 1.0000
16.750 1.2144 0.07689 0.07229 0.0171 0.0122 1.0000
17.000 1.2018 0.08254 0.07804 0.0145 0.0122 1.0000
17.250 1.1894 0.08828 0.08388 0.0118 0.0122 1.0000
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