NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 500,000 Max Cl/Cd: 66.18 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9627-il-500000.txt Download as CSV file: xf-npl9627-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9627 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7733 0.11156 0.10893 -0.0023 1.0000 0.0172
-14.000 -0.8005 0.10097 0.09829 -0.0081 1.0000 0.0170
-13.750 -0.8381 0.08810 0.08531 -0.0165 1.0000 0.0167
-13.500 -0.8751 0.07600 0.07303 -0.0254 1.0000 0.0164
-13.250 -0.9087 0.06544 0.06224 -0.0338 1.0000 0.0162
-13.000 -0.9399 0.05674 0.05327 -0.0402 1.0000 0.0160
-12.750 -0.9688 0.04989 0.04613 -0.0437 1.0000 0.0158
-12.500 -0.9915 0.04490 0.04085 -0.0444 1.0000 0.0157
-12.250 -1.0082 0.04111 0.03679 -0.0431 1.0000 0.0157
-12.000 -1.0192 0.03814 0.03357 -0.0406 1.0000 0.0157
-11.750 -1.0261 0.03556 0.03075 -0.0375 1.0000 0.0157
-11.500 -1.0263 0.03286 0.02776 -0.0350 1.0000 0.0157
-11.250 -1.0203 0.03055 0.02520 -0.0328 1.0000 0.0157
-11.000 -1.0100 0.02866 0.02311 -0.0310 1.0000 0.0157
-10.750 -0.9969 0.02705 0.02133 -0.0293 1.0000 0.0158
-10.500 -0.9822 0.02562 0.01975 -0.0278 1.0000 0.0160
-10.250 -0.9663 0.02432 0.01833 -0.0263 1.0000 0.0162
-10.000 -0.9496 0.02314 0.01702 -0.0247 1.0000 0.0164
-9.750 -0.9325 0.02204 0.01580 -0.0232 1.0000 0.0167
-9.500 -0.9150 0.02105 0.01469 -0.0216 1.0000 0.0171
-9.250 -0.8984 0.02005 0.01361 -0.0199 1.0000 0.0175
-9.000 -0.8805 0.01933 0.01290 -0.0183 1.0000 0.0179
-8.750 -0.8615 0.01878 0.01232 -0.0168 1.0000 0.0185
-8.500 -0.8427 0.01820 0.01168 -0.0153 1.0000 0.0195
-8.250 -0.8244 0.01757 0.01095 -0.0135 1.0000 0.0205
-8.000 -0.8063 0.01701 0.01042 -0.0119 1.0000 0.0214
-7.750 -0.7870 0.01659 0.00996 -0.0103 1.0000 0.0226
-7.500 -0.7674 0.01622 0.00950 -0.0087 1.0000 0.0237
-7.250 -0.7505 0.01557 0.00888 -0.0069 1.0000 0.0246
-7.000 -0.7316 0.01517 0.00846 -0.0053 1.0000 0.0257
-6.750 -0.7122 0.01482 0.00805 -0.0037 1.0000 0.0269
-6.500 -0.6943 0.01428 0.00752 -0.0020 1.0000 0.0282
-6.250 -0.6706 0.01388 0.00711 -0.0014 0.9994 0.0297
-6.000 -0.6350 0.01337 0.00657 -0.0032 0.9968 0.0320
-5.750 -0.5983 0.01297 0.00618 -0.0053 0.9943 0.0349
-5.500 -0.5616 0.01249 0.00570 -0.0073 0.9916 0.0377
-5.250 -0.5252 0.01215 0.00534 -0.0092 0.9874 0.0404
-5.000 -0.4876 0.01170 0.00491 -0.0114 0.9839 0.0435
-4.750 -0.4489 0.01134 0.00456 -0.0137 0.9813 0.0474
-4.500 -0.4135 0.01097 0.00422 -0.0153 0.9771 0.0533
-4.250 -0.3794 0.01033 0.00380 -0.0169 0.9720 0.0880
-4.000 -0.3464 0.00940 0.00340 -0.0184 0.9676 0.1938
-3.750 -0.3173 0.00890 0.00317 -0.0188 0.9594 0.2543
-3.500 -0.2855 0.00852 0.00298 -0.0197 0.9523 0.3028
-3.250 -0.2581 0.00824 0.00285 -0.0194 0.9409 0.3427
-3.000 -0.2300 0.00802 0.00272 -0.0193 0.9296 0.3749
-2.750 -0.2023 0.00785 0.00258 -0.0190 0.9174 0.4004
-2.500 -0.1761 0.00767 0.00245 -0.0183 0.9020 0.4236
-2.250 -0.1503 0.00749 0.00232 -0.0176 0.8842 0.4498
-2.000 -0.1250 0.00730 0.00220 -0.0168 0.8649 0.4825
-1.750 -0.0998 0.00709 0.00209 -0.0161 0.8454 0.5244
-1.500 -0.0754 0.00684 0.00201 -0.0151 0.8253 0.5819
-1.250 -0.0514 0.00661 0.00196 -0.0141 0.8041 0.6490
-1.000 -0.0274 0.00644 0.00193 -0.0129 0.7814 0.7092
-0.750 -0.0028 0.00636 0.00192 -0.0119 0.7586 0.7586
-0.500 0.0225 0.00632 0.00194 -0.0109 0.7373 0.7977
0.000 0.0738 0.00639 0.00200 -0.0092 0.6934 0.8569
0.250 0.0996 0.00648 0.00203 -0.0084 0.6715 0.8803
0.500 0.1257 0.00658 0.00208 -0.0076 0.6519 0.9002
0.750 0.1524 0.00669 0.00215 -0.0070 0.6342 0.9172
1.000 0.1802 0.00683 0.00222 -0.0066 0.6159 0.9315
1.250 0.2095 0.00697 0.00230 -0.0065 0.5959 0.9431
1.500 0.2390 0.00712 0.00238 -0.0066 0.5762 0.9538
1.750 0.2716 0.00729 0.00246 -0.0074 0.5558 0.9619
2.000 0.3052 0.00745 0.00255 -0.0085 0.5358 0.9687
2.250 0.3427 0.00764 0.00263 -0.0104 0.5133 0.9731
2.500 0.3780 0.00782 0.00272 -0.0120 0.4922 0.9786
2.750 0.4163 0.00798 0.00280 -0.0142 0.4674 0.9821
3.000 0.4549 0.00819 0.00288 -0.0165 0.4377 0.9854
3.250 0.4919 0.00839 0.00298 -0.0185 0.4098 0.9895
3.500 0.5283 0.00862 0.00308 -0.0205 0.3798 0.9933
3.750 0.5675 0.00889 0.00320 -0.0231 0.3416 0.9962
4.000 0.6061 0.00924 0.00335 -0.0256 0.3013 0.9995
4.250 0.6314 0.00954 0.00349 -0.0254 0.2657 1.0000
4.500 0.6532 0.00991 0.00367 -0.0244 0.2243 1.0000
4.750 0.6729 0.01052 0.00395 -0.0232 0.1608 1.0000
5.000 0.6923 0.01112 0.00428 -0.0219 0.1179 1.0000
5.250 0.7131 0.01150 0.00456 -0.0207 0.1045 1.0000
5.500 0.7345 0.01180 0.00483 -0.0195 0.0980 1.0000
5.750 0.7557 0.01211 0.00511 -0.0182 0.0935 1.0000
6.000 0.7764 0.01247 0.00545 -0.0169 0.0898 1.0000
6.250 0.7981 0.01273 0.00574 -0.0158 0.0877 1.0000
6.500 0.8195 0.01303 0.00605 -0.0146 0.0854 1.0000
6.750 0.8404 0.01339 0.00641 -0.0133 0.0829 1.0000
7.000 0.8595 0.01393 0.00693 -0.0118 0.0801 1.0000
7.250 0.8816 0.01421 0.00725 -0.0107 0.0784 1.0000
7.500 0.9032 0.01453 0.00760 -0.0096 0.0764 1.0000
7.750 0.9245 0.01490 0.00800 -0.0084 0.0742 1.0000
8.000 0.9440 0.01546 0.00854 -0.0071 0.0718 1.0000
8.250 0.9643 0.01599 0.00910 -0.0059 0.0696 1.0000
8.500 0.9870 0.01631 0.00947 -0.0050 0.0673 1.0000
8.750 1.0089 0.01671 0.00988 -0.0041 0.0649 1.0000
9.000 1.0257 0.01761 0.01075 -0.0026 0.0621 1.0000
9.250 1.0496 0.01783 0.01106 -0.0020 0.0600 1.0000
9.500 1.0719 0.01819 0.01145 -0.0012 0.0575 1.0000
9.750 1.0917 0.01876 0.01201 -0.0001 0.0555 1.0000
10.000 1.1113 0.01938 0.01268 0.0010 0.0535 1.0000
10.250 1.1331 0.01976 0.01312 0.0018 0.0516 1.0000
10.500 1.1543 0.02016 0.01354 0.0027 0.0498 1.0000
10.750 1.1713 0.02090 0.01426 0.0040 0.0483 1.0000
11.000 1.1904 0.02146 0.01491 0.0051 0.0471 1.0000
11.250 1.2090 0.02202 0.01555 0.0063 0.0458 1.0000
11.500 1.2264 0.02258 0.01616 0.0076 0.0447 1.0000
11.750 1.2416 0.02316 0.01678 0.0092 0.0437 1.0000
12.000 1.2535 0.02399 0.01762 0.0112 0.0428 1.0000
12.250 1.2649 0.02494 0.01863 0.0130 0.0420 1.0000
12.500 1.2784 0.02573 0.01954 0.0145 0.0412 1.0000
12.750 1.2915 0.02657 0.02046 0.0159 0.0402 1.0000
13.000 1.3043 0.02744 0.02138 0.0171 0.0393 1.0000
13.250 1.3163 0.02839 0.02238 0.0182 0.0385 1.0000
13.500 1.3239 0.02978 0.02378 0.0194 0.0376 1.0000
13.750 1.3326 0.03117 0.02528 0.0204 0.0369 1.0000
14.000 1.3418 0.03258 0.02681 0.0212 0.0361 1.0000
14.250 1.3501 0.03412 0.02846 0.0217 0.0354 1.0000
14.500 1.3576 0.03581 0.03023 0.0221 0.0347 1.0000
14.750 1.3640 0.03768 0.03217 0.0223 0.0341 1.0000
15.000 1.3681 0.03987 0.03441 0.0223 0.0335 1.0000
15.250 1.3678 0.04254 0.03711 0.0225 0.0329 1.0000
15.500 1.3697 0.04516 0.03987 0.0221 0.0325 1.0000
15.750 1.3709 0.04797 0.04284 0.0216 0.0320 1.0000
16.000 1.3707 0.05098 0.04598 0.0208 0.0315 1.0000
16.250 1.3694 0.05421 0.04933 0.0199 0.0310 1.0000
16.500 1.3672 0.05761 0.05284 0.0188 0.0306 1.0000
16.750 1.3639 0.06120 0.05652 0.0176 0.0301 1.0000
17.000 1.3599 0.06494 0.06035 0.0162 0.0298 1.0000
17.250 1.3549 0.06890 0.06437 0.0147 0.0294 1.0000
17.500 1.3486 0.07294 0.06846 0.0134 0.0290 1.0000
17.750 1.3395 0.07749 0.07311 0.0118 0.0286 1.0000
18.000 1.3286 0.08283 0.07862 0.0092 0.0284 1.0000
18.250 1.3164 0.08844 0.08439 0.0064 0.0281 1.0000
18.500 1.3027 0.09446 0.09057 0.0033 0.0279 1.0000
18.750 1.2880 0.10079 0.09705 0.0000 0.0276 1.0000
19.000 1.2719 0.10747 0.10388 -0.0035 0.0274 1.0000
19.250 1.2548 0.11451 0.11107 -0.0074 0.0271 1.0000
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Polar data table (+)
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