NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 200,000 Max Cl/Cd: 41.04 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nplx-il-200000.txt Download as CSV file: xf-nplx-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NPL AIRFOIL FROM ARC CP 1372
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5872 0.10286 0.09886 -0.0355 1.0000 0.0549
-10.250 -0.6080 0.09608 0.09207 -0.0411 1.0000 0.0550
-10.000 -0.6287 0.09088 0.08682 -0.0447 1.0000 0.0551
-9.750 -0.5955 0.08761 0.08370 -0.0394 1.0000 0.0564
-9.500 -0.5871 0.08549 0.08161 -0.0380 1.0000 0.0574
-9.250 -0.6004 0.07979 0.07591 -0.0415 1.0000 0.0577
-9.000 -0.6148 0.07498 0.07109 -0.0438 1.0000 0.0583
-8.750 -0.6418 0.07030 0.06637 -0.0456 1.0000 0.0582
-8.500 -0.6634 0.06725 0.06328 -0.0444 1.0000 0.0585
-8.250 -0.6748 0.06413 0.06010 -0.0433 1.0000 0.0592
-8.000 -0.6832 0.06110 0.05698 -0.0419 1.0000 0.0601
-7.750 -0.6893 0.05810 0.05385 -0.0403 1.0000 0.0615
-7.500 -0.7389 0.04313 0.03738 -0.0348 1.0000 0.0379
-7.250 -0.7250 0.04034 0.03459 -0.0335 1.0000 0.0360
-7.000 -0.7179 0.03671 0.03069 -0.0315 1.0000 0.0347
-6.750 -0.7099 0.03225 0.02572 -0.0291 1.0000 0.0330
-6.500 -0.6969 0.02878 0.02174 -0.0270 1.0000 0.0324
-6.250 -0.6800 0.02675 0.01946 -0.0254 1.0000 0.0327
-6.000 -0.6618 0.02534 0.01790 -0.0240 1.0000 0.0336
-5.750 -0.6429 0.02412 0.01648 -0.0225 1.0000 0.0355
-5.500 -0.6233 0.02302 0.01510 -0.0210 1.0000 0.0370
-5.250 -0.6041 0.02116 0.01320 -0.0197 1.0000 0.0388
-5.000 -0.5845 0.02022 0.01227 -0.0184 1.0000 0.0412
-4.750 -0.5641 0.01947 0.01137 -0.0170 1.0000 0.0453
-4.500 -0.5451 0.01827 0.01027 -0.0158 1.0000 0.0497
-4.250 -0.5244 0.01787 0.00977 -0.0147 1.0000 0.0549
-4.000 -0.5049 0.01715 0.00916 -0.0137 1.0000 0.0616
-3.750 -0.4845 0.01664 0.00862 -0.0127 1.0000 0.0680
-3.500 -0.4638 0.01628 0.00830 -0.0119 1.0000 0.0756
-3.250 -0.4431 0.01565 0.00770 -0.0110 1.0000 0.0829
-3.000 -0.4217 0.01520 0.00726 -0.0102 1.0000 0.0912
-2.750 -0.4001 0.01458 0.00671 -0.0097 1.0000 0.1040
-2.500 -0.3738 0.01390 0.00617 -0.0101 0.9991 0.1315
-2.250 -0.3453 0.01183 0.00588 -0.0121 0.9966 0.5316
-2.000 -0.3111 0.01222 0.00632 -0.0132 0.9928 0.5889
-1.750 -0.2776 0.01256 0.00666 -0.0142 0.9882 0.6166
-1.500 -0.2404 0.01294 0.00703 -0.0160 0.9841 0.6374
-1.250 -0.2086 0.01314 0.00722 -0.0167 0.9787 0.6527
-1.000 -0.1745 0.01343 0.00755 -0.0178 0.9745 0.6689
-0.750 -0.1412 0.01372 0.00785 -0.0188 0.9706 0.6840
-0.500 -0.1119 0.01382 0.00802 -0.0190 0.9651 0.6926
-0.250 -0.0737 0.01393 0.00811 -0.0211 0.9609 0.7020
0.000 -0.0391 0.01394 0.00816 -0.0223 0.9539 0.7096
0.250 0.0064 0.01381 0.00800 -0.0258 0.9472 0.7164
0.500 0.0444 0.01362 0.00785 -0.0276 0.9391 0.7199
0.750 0.0874 0.01340 0.00767 -0.0304 0.9331 0.7240
1.000 0.1287 0.01323 0.00752 -0.0330 0.9278 0.7293
1.250 0.1738 0.01283 0.00717 -0.0359 0.9186 0.7338
1.500 0.2243 0.01229 0.00672 -0.0396 0.9091 0.7380
1.750 0.2750 0.01175 0.00625 -0.0433 0.9002 0.7430
2.000 0.3142 0.01124 0.00577 -0.0445 0.8812 0.7485
2.250 0.3490 0.01073 0.00529 -0.0443 0.8486 0.7533
2.500 0.3803 0.01050 0.00501 -0.0440 0.8101 0.7597
2.750 0.4075 0.01042 0.00485 -0.0430 0.7639 0.7659
3.000 0.4305 0.01049 0.00471 -0.0411 0.6774 0.7720
3.250 0.4377 0.01165 0.00467 -0.0365 0.4351 0.7795
3.500 0.4414 0.01354 0.00521 -0.0325 0.1607 0.7859
3.750 0.4604 0.01452 0.00582 -0.0310 0.1087 0.7945
4.000 0.4811 0.01512 0.00640 -0.0295 0.0942 0.8022
4.250 0.5036 0.01565 0.00692 -0.0284 0.0862 0.8120
4.500 0.5243 0.01639 0.00768 -0.0270 0.0813 0.8215
4.750 0.5475 0.01686 0.00822 -0.0259 0.0773 0.8318
5.000 0.5707 0.01739 0.00874 -0.0249 0.0733 0.8436
5.250 0.5930 0.01851 0.00983 -0.0239 0.0698 0.8562
5.500 0.6165 0.01916 0.01058 -0.0228 0.0683 0.8706
5.750 0.6395 0.01980 0.01135 -0.0215 0.0668 0.8877
6.000 0.6621 0.02052 0.01221 -0.0201 0.0655 0.9089
6.250 0.6889 0.02138 0.01323 -0.0196 0.0640 0.9387
6.500 0.7286 0.02245 0.01441 -0.0222 0.0617 1.0000
6.750 0.7580 0.02363 0.01557 -0.0231 0.0599 1.0000
7.000 0.7864 0.02540 0.01741 -0.0236 0.0589 1.0000
7.250 0.8128 0.02763 0.01979 -0.0237 0.0584 1.0000
7.500 0.8369 0.03001 0.02238 -0.0234 0.0582 1.0000
7.750 0.8595 0.03214 0.02475 -0.0227 0.0583 1.0000
8.000 0.8793 0.03485 0.02773 -0.0217 0.0581 1.0000
8.250 0.8963 0.03799 0.03115 -0.0205 0.0580 1.0000
8.500 0.9154 0.03953 0.03297 -0.0191 0.0586 1.0000
8.750 0.8435 0.04939 0.04486 -0.0103 0.0970 1.0000
9.000 0.8160 0.05067 0.04688 -0.0050 0.0911 1.0000
9.250 0.8073 0.05485 0.05121 -0.0034 0.0891 1.0000
9.500 0.7969 0.05870 0.05515 -0.0017 0.0876 1.0000
9.750 0.7824 0.06243 0.05895 0.0001 0.0867 1.0000
10.000 0.8965 0.07509 0.07096 -0.0065 0.0824 1.0000
10.250 0.8533 0.07734 0.07354 -0.0028 0.0816 1.0000
10.500 0.8107 0.08186 0.07823 -0.0025 0.0810 1.0000
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