NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 50,000 Max Cl/Cd: 28.05 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9660-il-50000.txt Download as CSV file: xf-npl9660-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4997 0.10643 0.09939 0.0180 1.0000 0.3781
-8.500 -0.4931 0.10344 0.09642 0.0188 1.0000 0.3993
-8.250 -0.5048 0.10198 0.09505 0.0199 1.0000 0.4227
-8.000 -0.4855 0.09762 0.09071 0.0209 1.0000 0.4441
-7.750 -0.4623 0.09395 0.08701 0.0223 1.0000 0.4737
-7.500 -0.4594 0.09118 0.08430 0.0238 1.0000 0.4998
-7.250 -0.4485 0.08764 0.08078 0.0243 1.0000 0.5188
-7.000 -0.4355 0.08342 0.07656 0.0234 1.0000 0.5238
-6.750 -0.6231 0.05466 0.04672 -0.0215 1.0000 0.1640
-6.500 -0.6166 0.05022 0.04159 -0.0203 1.0000 0.1483
-6.250 -0.6039 0.04635 0.03744 -0.0189 1.0000 0.1425
-6.000 -0.5917 0.04295 0.03345 -0.0170 1.0000 0.1377
-5.750 -0.5761 0.04037 0.03063 -0.0154 1.0000 0.1414
-5.500 -0.5595 0.03805 0.02791 -0.0137 1.0000 0.1461
-5.250 -0.5423 0.03595 0.02530 -0.0120 1.0000 0.1524
-5.000 -0.5214 0.03346 0.02282 -0.0109 1.0000 0.1583
-4.750 -0.4989 0.03151 0.02058 -0.0096 1.0000 0.1617
-4.500 -0.4758 0.02997 0.01870 -0.0083 1.0000 0.1668
-4.250 -0.4511 0.02830 0.01685 -0.0073 1.0000 0.1709
-4.000 -0.4262 0.02685 0.01545 -0.0064 1.0000 0.1783
-3.750 -0.4001 0.02577 0.01426 -0.0054 1.0000 0.1844
-3.500 -0.3745 0.02463 0.01322 -0.0045 1.0000 0.1934
-3.250 -0.3505 0.02380 0.01231 -0.0033 1.0000 0.2046
-3.000 -0.3293 0.02278 0.01145 -0.0021 1.0000 0.2181
-2.750 -0.3105 0.02176 0.01065 -0.0006 1.0000 0.2429
-2.500 -0.0229 0.02212 0.01284 -0.0282 1.0000 1.0000
-2.250 -0.0140 0.02168 0.01232 -0.0267 1.0000 1.0000
-2.000 -0.0087 0.02133 0.01192 -0.0246 1.0000 1.0000
-1.750 -0.0072 0.02106 0.01161 -0.0218 1.0000 1.0000
-1.500 -0.0083 0.02086 0.01136 -0.0185 1.0000 1.0000
-1.250 -0.0118 0.02073 0.01120 -0.0148 1.0000 1.0000
-1.000 -0.0171 0.02067 0.01110 -0.0108 1.0000 1.0000
-0.750 -0.0234 0.02067 0.01107 -0.0066 1.0000 1.0000
-0.500 -0.0296 0.02075 0.01111 -0.0025 1.0000 1.0000
-0.250 -0.0346 0.02090 0.01121 0.0013 1.0000 1.0000
0.000 -0.0375 0.02112 0.01137 0.0048 1.0000 1.0000
0.250 -0.0380 0.02142 0.01160 0.0077 1.0000 1.0000
0.500 -0.0345 0.02179 0.01191 0.0099 1.0000 1.0000
0.750 -0.0273 0.02227 0.01231 0.0114 1.0000 1.0000
1.000 -0.0007 0.02300 0.01298 0.0093 0.9946 1.0000
1.250 0.0622 0.02416 0.01409 0.0009 0.9757 1.0000
1.500 0.1215 0.02525 0.01516 -0.0066 0.9552 1.0000
1.750 0.1795 0.02614 0.01608 -0.0133 0.9340 1.0000
2.000 0.2291 0.02678 0.01677 -0.0182 0.9105 1.0000
2.250 0.2922 0.02724 0.01733 -0.0249 0.8884 1.0000
2.500 0.3449 0.02750 0.01771 -0.0294 0.8646 1.0000
2.750 0.3959 0.02747 0.01781 -0.0328 0.8395 1.0000
3.000 0.4554 0.02684 0.01734 -0.0363 0.8157 1.0000
3.250 0.4861 0.02663 0.01722 -0.0354 0.7888 1.0000
3.500 0.5243 0.02595 0.01664 -0.0346 0.7634 1.0000
3.750 0.5533 0.02551 0.01627 -0.0326 0.7368 1.0000
4.000 0.5798 0.02508 0.01588 -0.0299 0.7087 1.0000
4.250 0.6029 0.02484 0.01565 -0.0270 0.6784 1.0000
4.500 0.6275 0.02445 0.01522 -0.0238 0.6472 1.0000
4.750 0.6480 0.02440 0.01512 -0.0206 0.6115 1.0000
5.000 0.6685 0.02452 0.01512 -0.0175 0.5741 1.0000
5.250 0.6888 0.02484 0.01533 -0.0148 0.5353 1.0000
5.500 0.7084 0.02539 0.01576 -0.0124 0.4962 1.0000
5.750 0.7289 0.02599 0.01620 -0.0102 0.4599 1.0000
6.000 0.7495 0.02675 0.01685 -0.0083 0.4270 1.0000
6.250 0.7696 0.02775 0.01786 -0.0067 0.3976 1.0000
6.500 0.7918 0.02857 0.01852 -0.0052 0.3718 1.0000
6.750 0.8121 0.02971 0.01970 -0.0038 0.3474 1.0000
7.000 0.8325 0.03088 0.02092 -0.0025 0.3242 1.0000
7.250 0.8540 0.03196 0.02190 -0.0012 0.3015 1.0000
7.500 0.8738 0.03325 0.02315 0.0002 0.2783 1.0000
7.750 0.8914 0.03461 0.02460 0.0017 0.2538 1.0000
8.000 0.9123 0.03602 0.02573 0.0030 0.2296 1.0000
8.250 0.9259 0.03802 0.02800 0.0047 0.2072 1.0000
8.500 0.9418 0.04004 0.03009 0.0062 0.1869 1.0000
8.750 0.9568 0.04235 0.03251 0.0077 0.1704 1.0000
9.000 0.9690 0.04516 0.03555 0.0091 0.1583 1.0000
9.250 0.9854 0.04799 0.03842 0.0102 0.1492 1.0000
9.500 0.9859 0.05185 0.04286 0.0121 0.1438 1.0000
9.750 1.0020 0.05462 0.04560 0.0129 0.1369 1.0000
10.000 0.9910 0.05922 0.05077 0.0148 0.1347 1.0000
10.250 0.9757 0.06410 0.05606 0.0162 0.1336 1.0000
10.500 0.9523 0.06951 0.06178 0.0171 0.1340 1.0000
10.750 0.9226 0.07514 0.06760 0.0174 0.1353 1.0000
11.000 0.8949 0.08158 0.07414 0.0157 0.1367 1.0000
11.250 0.8739 0.08861 0.08122 0.0129 0.1378 1.0000
11.500 0.7055 0.14036 0.13275 -0.0309 0.2985 1.0000
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Polar data table (+)
Polar graphs
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