NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 200,000 Max Cl/Cd: 49.02 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9627-il-200000-n5.txt Download as CSV file: xf-npl9627-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8023 0.09206 0.08787 -0.0143 1.0000 0.0163
-13.250 -0.8576 0.07571 0.07122 -0.0261 1.0000 0.0160
-13.000 -0.8907 0.06533 0.06056 -0.0341 1.0000 0.0158
-12.750 -0.9142 0.05793 0.05289 -0.0394 1.0000 0.0158
-12.500 -0.9320 0.05244 0.04715 -0.0423 1.0000 0.0158
-12.250 -0.9457 0.04819 0.04265 -0.0433 1.0000 0.0159
-12.000 -0.9559 0.04478 0.03900 -0.0429 1.0000 0.0160
-11.750 -0.9631 0.04194 0.03591 -0.0415 1.0000 0.0161
-11.500 -0.9676 0.03947 0.03321 -0.0393 1.0000 0.0163
-11.250 -0.9690 0.03723 0.03072 -0.0367 1.0000 0.0166
-11.000 -0.9650 0.03497 0.02816 -0.0346 1.0000 0.0169
-10.750 -0.9570 0.03298 0.02591 -0.0327 1.0000 0.0173
-10.500 -0.9437 0.03182 0.02468 -0.0313 1.0000 0.0176
-10.250 -0.9293 0.03069 0.02345 -0.0299 1.0000 0.0180
-10.000 -0.9143 0.02950 0.02214 -0.0285 1.0000 0.0185
-9.750 -0.8987 0.02824 0.02072 -0.0270 1.0000 0.0192
-9.500 -0.8826 0.02691 0.01917 -0.0255 1.0000 0.0201
-9.250 -0.8654 0.02590 0.01809 -0.0241 1.0000 0.0207
-9.000 -0.8475 0.02507 0.01720 -0.0228 1.0000 0.0213
-8.750 -0.8295 0.02419 0.01625 -0.0214 1.0000 0.0222
-8.500 -0.8114 0.02329 0.01521 -0.0199 1.0000 0.0232
-8.250 -0.7936 0.02246 0.01433 -0.0184 1.0000 0.0241
-8.000 -0.7752 0.02181 0.01366 -0.0170 1.0000 0.0252
-7.750 -0.7563 0.02119 0.01294 -0.0155 1.0000 0.0268
-7.500 -0.7380 0.02054 0.01228 -0.0140 1.0000 0.0282
-7.250 -0.7193 0.01996 0.01166 -0.0125 1.0000 0.0299
-7.000 -0.7008 0.01933 0.01098 -0.0109 1.0000 0.0316
-6.750 -0.6827 0.01873 0.01039 -0.0093 1.0000 0.0333
-6.500 -0.6638 0.01820 0.00980 -0.0077 1.0000 0.0353
-6.250 -0.6457 0.01761 0.00921 -0.0061 1.0000 0.0371
-6.000 -0.6268 0.01712 0.00869 -0.0046 1.0000 0.0390
-5.750 -0.6009 0.01660 0.00812 -0.0045 0.9981 0.0412
-5.500 -0.5661 0.01606 0.00756 -0.0063 0.9937 0.0443
-5.250 -0.5324 0.01555 0.00703 -0.0078 0.9886 0.0480
-5.000 -0.4977 0.01507 0.00654 -0.0094 0.9834 0.0537
-4.750 -0.4631 0.01452 0.00605 -0.0111 0.9784 0.0654
-4.500 -0.4317 0.01372 0.00555 -0.0122 0.9715 0.1093
-4.250 -0.3978 0.01298 0.00515 -0.0140 0.9656 0.1800
-4.000 -0.3670 0.01250 0.00487 -0.0147 0.9560 0.2278
-3.750 -0.3347 0.01208 0.00464 -0.0158 0.9471 0.2754
-3.500 -0.3029 0.01170 0.00445 -0.0167 0.9373 0.3240
-3.250 -0.2730 0.01143 0.00430 -0.0171 0.9259 0.3614
-3.000 -0.2419 0.01117 0.00412 -0.0176 0.9149 0.3942
-2.750 -0.2122 0.01089 0.00394 -0.0178 0.9025 0.4274
-2.500 -0.1843 0.01062 0.00379 -0.0176 0.8882 0.4598
-2.250 -0.1565 0.01037 0.00363 -0.0174 0.8733 0.4915
-2.000 -0.1292 0.01014 0.00349 -0.0170 0.8572 0.5221
-1.750 -0.1028 0.00991 0.00337 -0.0164 0.8402 0.5587
-1.500 -0.0772 0.00970 0.00328 -0.0155 0.8219 0.6029
-1.000 -0.0270 0.00938 0.00317 -0.0134 0.7807 0.6974
-0.750 -0.0015 0.00931 0.00315 -0.0123 0.7604 0.7406
-0.500 0.0244 0.00929 0.00317 -0.0114 0.7409 0.7788
-0.250 0.0509 0.00932 0.00319 -0.0105 0.7213 0.8124
0.000 0.0785 0.00939 0.00324 -0.0099 0.7007 0.8407
0.250 0.1064 0.00949 0.00328 -0.0094 0.6800 0.8654
0.500 0.1358 0.00961 0.00333 -0.0093 0.6604 0.8855
0.750 0.1659 0.00974 0.00339 -0.0094 0.6427 0.9027
1.000 0.1962 0.00988 0.00345 -0.0095 0.6246 0.9178
1.250 0.2289 0.01003 0.00351 -0.0102 0.6046 0.9297
1.500 0.2612 0.01019 0.00357 -0.0109 0.5840 0.9406
2.000 0.3272 0.01052 0.00370 -0.0128 0.5384 0.9597
2.250 0.3599 0.01070 0.00378 -0.0137 0.5144 0.9681
2.500 0.3961 0.01089 0.00385 -0.0155 0.4890 0.9742
2.750 0.4302 0.01107 0.00394 -0.0168 0.4627 0.9812
3.000 0.4685 0.01127 0.00402 -0.0191 0.4337 0.9872
3.250 0.5065 0.01154 0.00413 -0.0214 0.3967 0.9941
3.500 0.5453 0.01182 0.00425 -0.0239 0.3591 0.9999
3.750 0.5677 0.01206 0.00438 -0.0230 0.3317 1.0000
4.000 0.5896 0.01233 0.00453 -0.0220 0.3055 1.0000
4.250 0.6113 0.01262 0.00471 -0.0210 0.2793 1.0000
4.500 0.6325 0.01296 0.00492 -0.0199 0.2514 1.0000
4.750 0.6535 0.01333 0.00517 -0.0188 0.2215 1.0000
5.000 0.6738 0.01380 0.00546 -0.0175 0.1860 1.0000
5.250 0.6934 0.01433 0.00580 -0.0162 0.1509 1.0000
6.000 0.7543 0.01575 0.00697 -0.0125 0.1058 1.0000
6.250 0.7746 0.01621 0.00741 -0.0112 0.0999 1.0000
6.500 0.7953 0.01664 0.00783 -0.0100 0.0947 1.0000
6.750 0.8150 0.01717 0.00831 -0.0087 0.0901 1.0000
7.000 0.8362 0.01758 0.00877 -0.0076 0.0863 1.0000
7.250 0.8567 0.01806 0.00927 -0.0064 0.0830 1.0000
7.500 0.8759 0.01868 0.00986 -0.0051 0.0802 1.0000
7.750 0.8968 0.01916 0.01040 -0.0040 0.0779 1.0000
8.000 0.9174 0.01968 0.01097 -0.0030 0.0755 1.0000
8.250 0.9374 0.02026 0.01158 -0.0018 0.0732 1.0000
8.500 0.9559 0.02097 0.01229 -0.0006 0.0711 1.0000
8.750 0.9756 0.02160 0.01298 0.0006 0.0691 1.0000
9.000 0.9955 0.02220 0.01365 0.0017 0.0667 1.0000
9.250 1.0146 0.02285 0.01435 0.0028 0.0645 1.0000
9.500 1.0320 0.02364 0.01513 0.0041 0.0626 1.0000
9.750 1.0504 0.02438 0.01596 0.0053 0.0607 1.0000
10.000 1.0686 0.02511 0.01679 0.0065 0.0587 1.0000
10.250 1.0858 0.02587 0.01762 0.0077 0.0569 1.0000
10.500 1.1019 0.02669 0.01846 0.0091 0.0554 1.0000
10.750 1.1173 0.02760 0.01944 0.0105 0.0539 1.0000
11.000 1.1319 0.02843 0.02042 0.0120 0.0522 1.0000
11.250 1.1449 0.02930 0.02139 0.0137 0.0507 1.0000
11.500 1.1572 0.03021 0.02235 0.0154 0.0495 1.0000
11.750 1.1686 0.03119 0.02337 0.0169 0.0485 1.0000
12.000 1.1797 0.03234 0.02464 0.0184 0.0474 1.0000
12.250 1.1902 0.03355 0.02602 0.0198 0.0460 1.0000
12.500 1.1998 0.03479 0.02737 0.0211 0.0449 1.0000
12.750 1.2086 0.03607 0.02875 0.0222 0.0439 1.0000
13.000 1.2168 0.03743 0.03018 0.0231 0.0431 1.0000
13.250 1.2239 0.03898 0.03178 0.0238 0.0424 1.0000
13.500 1.2292 0.04092 0.03394 0.0245 0.0413 1.0000
13.750 1.2337 0.04296 0.03614 0.0250 0.0404 1.0000
14.000 1.2374 0.04511 0.03843 0.0252 0.0396 1.0000
14.250 1.2406 0.04737 0.04082 0.0251 0.0389 1.0000
14.500 1.2431 0.04979 0.04333 0.0248 0.0383 1.0000
14.750 1.2448 0.05237 0.04600 0.0242 0.0378 1.0000
15.000 1.2454 0.05518 0.04886 0.0236 0.0374 1.0000
15.250 1.2402 0.05893 0.05286 0.0225 0.0368 1.0000
15.500 1.2335 0.06298 0.05711 0.0212 0.0362 1.0000
15.750 1.2254 0.06736 0.06168 0.0194 0.0357 1.0000
16.000 1.2157 0.07206 0.06656 0.0174 0.0353 1.0000
16.250 1.2046 0.07719 0.07186 0.0149 0.0349 1.0000
16.500 1.1920 0.08278 0.07761 0.0121 0.0346 1.0000
16.750 1.1776 0.08886 0.08386 0.0089 0.0343 1.0000
17.000 1.1610 0.09562 0.09077 0.0051 0.0340 1.0000
17.250 1.1405 0.10336 0.09868 0.0007 0.0338 1.0000
17.500 1.1105 0.11340 0.10891 -0.0053 0.0336 1.0000
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