USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 500,000 Max Cl/Cd: 87.16 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usnps4-il-500000-n5.txt Download as CSV file: xf-usnps4-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USNPS4 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1633 0.08507 0.08265 -0.0793 0.9752 0.0107
-8.250 -0.1629 0.08140 0.07900 -0.0808 0.9694 0.0108
-7.750 -0.1519 0.07106 0.06866 -0.0915 0.9602 0.0110
-7.500 -0.1466 0.06261 0.06016 -0.1012 0.9534 0.0115
-7.000 -0.1095 0.05629 0.05376 -0.1085 0.9456 0.0120
-6.500 -0.1101 0.02136 0.01691 -0.1211 0.9311 0.0144
-6.250 -0.0802 0.02098 0.01651 -0.1218 0.9279 0.0147
-6.000 -0.0467 0.02045 0.01592 -0.1234 0.9256 0.0151
-5.750 -0.0142 0.01835 0.01348 -0.1251 0.9235 0.0158
-5.500 0.0058 0.01638 0.01112 -0.1237 0.9159 0.0165
-5.250 0.0376 0.01487 0.00928 -0.1247 0.9118 0.0172
-5.000 0.0709 0.01389 0.00805 -0.1259 0.9074 0.0176
-4.750 0.0987 0.01327 0.00737 -0.1260 0.8996 0.0183
-4.500 0.1347 0.01286 0.00691 -0.1278 0.8941 0.0190
-4.250 0.1641 0.01244 0.00641 -0.1281 0.8844 0.0198
-4.000 0.1966 0.01188 0.00572 -0.1291 0.8751 0.0205
-3.750 0.2294 0.01140 0.00511 -0.1301 0.8642 0.0212
-3.500 0.2600 0.01096 0.00459 -0.1307 0.8508 0.0220
-3.250 0.2899 0.01070 0.00426 -0.1311 0.8358 0.0228
-3.000 0.3189 0.01053 0.00399 -0.1313 0.8189 0.0240
-2.750 0.3468 0.01037 0.00371 -0.1312 0.8005 0.0254
-2.500 0.3736 0.01018 0.00343 -0.1309 0.7804 0.0267
-2.250 0.3998 0.01011 0.00325 -0.1305 0.7596 0.0281
-2.000 0.4254 0.01006 0.00309 -0.1299 0.7378 0.0298
-1.750 0.4504 0.01003 0.00294 -0.1293 0.7153 0.0318
-1.500 0.4750 0.01006 0.00287 -0.1285 0.6923 0.0346
-1.250 0.4995 0.01011 0.00279 -0.1277 0.6690 0.0374
-1.000 0.5236 0.01014 0.00273 -0.1269 0.6457 0.0410
-0.750 0.5478 0.01022 0.00269 -0.1261 0.6220 0.0448
-0.500 0.5717 0.01030 0.00268 -0.1253 0.5988 0.0502
-0.250 0.5959 0.01040 0.00268 -0.1245 0.5760 0.0558
0.000 0.6197 0.01051 0.00269 -0.1237 0.5535 0.0638
0.250 0.6441 0.01060 0.00272 -0.1230 0.5318 0.0746
0.500 0.6682 0.01071 0.00276 -0.1223 0.5105 0.0922
0.750 0.6921 0.01070 0.00283 -0.1216 0.4902 0.1650
1.000 0.7027 0.00906 0.00318 -0.1183 0.4745 0.9025
1.250 0.7378 0.00919 0.00323 -0.1198 0.4544 1.0000
1.500 0.7615 0.00941 0.00330 -0.1191 0.4366 1.0000
1.750 0.7855 0.00962 0.00339 -0.1183 0.4205 1.0000
2.000 0.8096 0.00983 0.00349 -0.1176 0.4058 1.0000
2.250 0.8337 0.01005 0.00359 -0.1169 0.3911 1.0000
2.500 0.8576 0.01028 0.00371 -0.1162 0.3771 1.0000
3.000 0.9060 0.01071 0.00397 -0.1149 0.3529 1.0000
3.250 0.9300 0.01093 0.00411 -0.1142 0.3415 1.0000
3.500 0.9537 0.01116 0.00427 -0.1135 0.3305 1.0000
3.750 0.9774 0.01139 0.00443 -0.1128 0.3202 1.0000
4.000 1.0013 0.01160 0.00459 -0.1121 0.3117 1.0000
4.500 1.0480 0.01207 0.00496 -0.1106 0.2939 1.0000
4.750 1.0702 0.01233 0.00515 -0.1096 0.2856 1.0000
5.000 1.0929 0.01255 0.00535 -0.1087 0.2782 1.0000
5.250 1.1147 0.01282 0.00558 -0.1076 0.2714 1.0000
5.500 1.1374 0.01305 0.00580 -0.1067 0.2650 1.0000
5.750 1.1589 0.01333 0.00604 -0.1057 0.2581 1.0000
6.000 1.1811 0.01359 0.00629 -0.1047 0.2518 1.0000
6.250 1.2029 0.01388 0.00655 -0.1037 0.2452 1.0000
6.500 1.2244 0.01417 0.00684 -0.1027 0.2400 1.0000
6.750 1.2464 0.01444 0.00711 -0.1018 0.2348 1.0000
7.000 1.2675 0.01476 0.00742 -0.1007 0.2296 1.0000
7.250 1.2886 0.01508 0.00774 -0.0997 0.2250 1.0000
7.500 1.3100 0.01538 0.00805 -0.0987 0.2199 1.0000
7.750 1.3303 0.01574 0.00840 -0.0975 0.2147 1.0000
8.000 1.3507 0.01609 0.00877 -0.0964 0.2105 1.0000
8.250 1.3715 0.01642 0.00913 -0.0954 0.2065 1.0000
8.500 1.3915 0.01679 0.00951 -0.0942 0.2024 1.0000
8.750 1.4103 0.01722 0.00995 -0.0929 0.1985 1.0000
9.000 1.4304 0.01758 0.01036 -0.0918 0.1954 1.0000
9.250 1.4501 0.01797 0.01079 -0.0907 0.1916 1.0000
9.500 1.4686 0.01842 0.01126 -0.0894 0.1876 1.0000
9.750 1.4857 0.01894 0.01180 -0.0879 0.1839 1.0000
10.000 1.5050 0.01935 0.01227 -0.0867 0.1813 1.0000
10.250 1.5235 0.01980 0.01278 -0.0855 0.1783 1.0000
10.500 1.5410 0.02032 0.01335 -0.0842 0.1752 1.0000
10.750 1.5572 0.02090 0.01397 -0.0827 0.1722 1.0000
11.000 1.5737 0.02147 0.01458 -0.0812 0.1680 1.0000
11.250 1.5903 0.02205 0.01519 -0.0799 0.1620 1.0000
11.500 1.6039 0.02281 0.01595 -0.0782 0.1562 1.0000
11.750 1.6205 0.02340 0.01660 -0.0769 0.1516 1.0000
12.000 1.6347 0.02413 0.01737 -0.0753 0.1468 1.0000
12.250 1.6477 0.02496 0.01823 -0.0737 0.1424 1.0000
12.500 1.6622 0.02571 0.01904 -0.0722 0.1371 1.0000
12.750 1.6731 0.02670 0.02005 -0.0705 0.1313 1.0000
13.000 1.6857 0.02761 0.02101 -0.0689 0.1250 1.0000
13.250 1.6943 0.02880 0.02220 -0.0671 0.1178 1.0000
13.500 1.7025 0.03006 0.02346 -0.0652 0.1083 1.0000
13.750 1.7072 0.03162 0.02501 -0.0632 0.0969 1.0000
14.000 1.7078 0.03357 0.02691 -0.0609 0.0833 1.0000
14.250 1.7016 0.03615 0.02942 -0.0583 0.0658 1.0000
14.500 1.6910 0.03930 0.03251 -0.0557 0.0496 1.0000
14.750 1.6787 0.04282 0.03602 -0.0534 0.0370 1.0000
15.000 1.6704 0.04614 0.03937 -0.0518 0.0296 1.0000
15.250 1.6639 0.04947 0.04276 -0.0506 0.0251 1.0000
15.500 1.6575 0.05294 0.04632 -0.0498 0.0219 1.0000
15.750 1.6525 0.05640 0.04988 -0.0493 0.0197 1.0000
16.000 1.6451 0.06027 0.05385 -0.0490 0.0180 1.0000
16.250 1.6378 0.06427 0.05797 -0.0490 0.0167 1.0000
16.500 1.6296 0.06853 0.06236 -0.0493 0.0156 1.0000
16.750 1.6190 0.07324 0.06719 -0.0498 0.0147 1.0000
17.000 1.6059 0.07842 0.07250 -0.0507 0.0140 1.0000
17.250 1.5938 0.08358 0.07780 -0.0517 0.0135 1.0000
17.500 1.5802 0.08906 0.08342 -0.0529 0.0130 1.0000
17.750 1.5653 0.09486 0.08936 -0.0544 0.0126 1.0000
18.000 1.5491 0.10091 0.09555 -0.0561 0.0122 1.0000
18.250 1.5318 0.10724 0.10201 -0.0581 0.0119 1.0000
18.500 1.5144 0.11369 0.10860 -0.0603 0.0117 1.0000
|
Polar data table (+)
Polar graphs
<< Back to USNPS4 (smoothed) (usnps4-il)