USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.32 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usnps4-il-1000000-n5.txt Download as CSV file: xf-usnps4-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3394 0.02062 0.01716 -0.1296 0.9562 0.0103
-8.750 -0.3157 0.01834 0.01457 -0.1300 0.9541 0.0107
-8.500 -0.2886 0.01683 0.01282 -0.1307 0.9525 0.0109
-8.250 -0.2597 0.01567 0.01146 -0.1315 0.9511 0.0112
-8.000 -0.2343 0.01486 0.01050 -0.1313 0.9480 0.0113
-7.750 -0.2105 0.01406 0.00956 -0.1307 0.9435 0.0116
-7.500 -0.1821 0.01337 0.00878 -0.1310 0.9405 0.0119
-7.250 -0.1506 0.01286 0.00820 -0.1320 0.9381 0.0121
-7.000 -0.1228 0.01246 0.00774 -0.1321 0.9340 0.0124
-6.750 -0.0954 0.01206 0.00728 -0.1321 0.9286 0.0127
-6.500 -0.0638 0.01165 0.00680 -0.1330 0.9243 0.0131
-6.250 -0.0358 0.01128 0.00636 -0.1330 0.9177 0.0135
-6.000 -0.0055 0.01089 0.00587 -0.1336 0.9108 0.0139
-5.750 0.0233 0.01053 0.00542 -0.1338 0.9023 0.0141
-5.500 0.0530 0.01016 0.00495 -0.1342 0.8929 0.0144
-5.250 0.0814 0.00977 0.00448 -0.1343 0.8810 0.0149
-5.000 0.1096 0.00954 0.00417 -0.1344 0.8673 0.0153
-4.750 0.1374 0.00936 0.00391 -0.1343 0.8516 0.0157
-4.500 0.1645 0.00922 0.00367 -0.1341 0.8342 0.0162
-4.250 0.1911 0.00911 0.00345 -0.1337 0.8154 0.0168
-4.000 0.2172 0.00902 0.00324 -0.1333 0.7952 0.0173
-3.750 0.2427 0.00895 0.00305 -0.1327 0.7743 0.0177
-3.500 0.2680 0.00883 0.00283 -0.1321 0.7528 0.0184
-3.250 0.2931 0.00880 0.00269 -0.1315 0.7300 0.0191
-3.000 0.3183 0.00880 0.00259 -0.1309 0.7077 0.0198
-2.750 0.3436 0.00880 0.00248 -0.1303 0.6847 0.0207
-2.500 0.3686 0.00884 0.00240 -0.1296 0.6614 0.0215
-2.250 0.3939 0.00884 0.00231 -0.1291 0.6380 0.0230
-2.000 0.4190 0.00890 0.00227 -0.1285 0.6149 0.0245
-1.750 0.4445 0.00896 0.00221 -0.1280 0.5918 0.0259
-1.500 0.4698 0.00902 0.00218 -0.1274 0.5689 0.0281
-1.250 0.4955 0.00909 0.00217 -0.1270 0.5470 0.0304
-1.000 0.5210 0.00917 0.00216 -0.1265 0.5252 0.0333
-0.750 0.5467 0.00926 0.00217 -0.1261 0.5046 0.0367
-0.500 0.5725 0.00935 0.00218 -0.1257 0.4846 0.0406
-0.250 0.5982 0.00945 0.00220 -0.1253 0.4647 0.0445
0.000 0.6241 0.00954 0.00223 -0.1249 0.4471 0.0503
0.250 0.6500 0.00964 0.00227 -0.1246 0.4305 0.0573
0.500 0.6757 0.00974 0.00232 -0.1242 0.4134 0.0662
0.750 0.7016 0.00983 0.00238 -0.1238 0.3983 0.0801
1.000 0.7276 0.00988 0.00244 -0.1236 0.3850 0.1101
1.500 0.7682 0.00834 0.00287 -0.1211 0.3599 0.9158
1.750 0.7995 0.00843 0.00294 -0.1218 0.3473 1.0000
2.000 0.8251 0.00858 0.00301 -0.1214 0.3366 1.0000
2.250 0.8505 0.00875 0.00310 -0.1210 0.3259 1.0000
2.500 0.8757 0.00894 0.00320 -0.1205 0.3152 1.0000
2.750 0.9011 0.00910 0.00330 -0.1201 0.3056 1.0000
3.000 0.9266 0.00927 0.00341 -0.1197 0.2979 1.0000
3.250 0.9517 0.00945 0.00353 -0.1192 0.2889 1.0000
3.500 0.9769 0.00963 0.00365 -0.1188 0.2807 1.0000
4.000 1.0267 0.00999 0.00391 -0.1178 0.2659 1.0000
4.250 1.0513 0.01018 0.00406 -0.1173 0.2590 1.0000
4.500 1.0761 0.01036 0.00421 -0.1168 0.2533 1.0000
4.750 1.1004 0.01056 0.00436 -0.1162 0.2463 1.0000
5.000 1.1243 0.01077 0.00454 -0.1156 0.2398 1.0000
5.250 1.1485 0.01095 0.00470 -0.1150 0.2341 1.0000
5.500 1.1715 0.01117 0.00488 -0.1142 0.2285 1.0000
5.750 1.1946 0.01136 0.00506 -0.1133 0.2242 1.0000
6.000 1.2175 0.01156 0.00526 -0.1125 0.2196 1.0000
6.250 1.2396 0.01181 0.00547 -0.1115 0.2142 1.0000
6.500 1.2621 0.01203 0.00568 -0.1106 0.2098 1.0000
6.750 1.2845 0.01226 0.00591 -0.1097 0.2049 1.0000
7.000 1.3064 0.01252 0.00615 -0.1088 0.2004 1.0000
7.250 1.3287 0.01276 0.00640 -0.1079 0.1967 1.0000
7.500 1.3511 0.01299 0.00664 -0.1071 0.1935 1.0000
7.750 1.3730 0.01325 0.00690 -0.1061 0.1897 1.0000
8.000 1.3940 0.01355 0.00719 -0.1051 0.1857 1.0000
8.250 1.4155 0.01383 0.00748 -0.1041 0.1824 1.0000
8.500 1.4371 0.01410 0.00777 -0.1032 0.1789 1.0000
8.750 1.4580 0.01440 0.00808 -0.1021 0.1753 1.0000
9.000 1.4782 0.01475 0.00843 -0.1010 0.1719 1.0000
9.250 1.4987 0.01507 0.00877 -0.0999 0.1691 1.0000
9.500 1.5195 0.01536 0.00911 -0.0989 0.1669 1.0000
9.750 1.5398 0.01569 0.00946 -0.0978 0.1642 1.0000
10.000 1.5585 0.01611 0.00988 -0.0965 0.1597 1.0000
10.250 1.5769 0.01654 0.01031 -0.0952 0.1534 1.0000
10.500 1.5947 0.01701 0.01077 -0.0938 0.1472 1.0000
10.750 1.6121 0.01749 0.01126 -0.0923 0.1428 1.0000
11.000 1.6303 0.01793 0.01172 -0.0911 0.1387 1.0000
11.250 1.6469 0.01847 0.01226 -0.0896 0.1335 1.0000
11.500 1.6633 0.01902 0.01283 -0.0880 0.1286 1.0000
11.750 1.6786 0.01963 0.01344 -0.0864 0.1222 1.0000
12.000 1.6927 0.02032 0.01412 -0.0846 0.1154 1.0000
12.250 1.7039 0.02119 0.01496 -0.0825 0.1058 1.0000
12.500 1.7133 0.02220 0.01591 -0.0802 0.0945 1.0000
12.750 1.7187 0.02347 0.01711 -0.0774 0.0795 1.0000
13.000 1.7174 0.02523 0.01875 -0.0739 0.0614 1.0000
13.250 1.7084 0.02760 0.02100 -0.0697 0.0404 1.0000
13.500 1.7058 0.02962 0.02299 -0.0666 0.0291 1.0000
13.750 1.7069 0.03144 0.02483 -0.0641 0.0228 1.0000
14.000 1.7098 0.03321 0.02664 -0.0620 0.0188 1.0000
14.250 1.7135 0.03498 0.02845 -0.0602 0.0164 1.0000
14.500 1.7170 0.03683 0.03035 -0.0585 0.0145 1.0000
14.750 1.7209 0.03873 0.03232 -0.0570 0.0132 1.0000
15.000 1.7242 0.04077 0.03443 -0.0557 0.0120 1.0000
15.250 1.7256 0.04307 0.03680 -0.0545 0.0110 1.0000
15.500 1.7279 0.04536 0.03917 -0.0534 0.0103 1.0000
15.750 1.7284 0.04791 0.04180 -0.0525 0.0097 1.0000
16.000 1.7275 0.05073 0.04470 -0.0518 0.0091 1.0000
16.250 1.7249 0.05383 0.04789 -0.0512 0.0086 1.0000
16.500 1.7226 0.05701 0.05117 -0.0509 0.0082 1.0000
16.750 1.7188 0.06045 0.05471 -0.0507 0.0078 1.0000
17.000 1.7131 0.06423 0.05860 -0.0507 0.0075 1.0000
17.250 1.7054 0.06838 0.06284 -0.0510 0.0072 1.0000
17.500 1.6956 0.07294 0.06751 -0.0515 0.0069 1.0000
17.750 1.6838 0.07787 0.07256 -0.0522 0.0067 1.0000
18.000 1.6699 0.08318 0.07798 -0.0531 0.0065 1.0000
18.250 1.6564 0.08855 0.08349 -0.0543 0.0063 1.0000
18.500 1.6418 0.09418 0.08925 -0.0557 0.0062 1.0000
18.750 1.6252 0.10017 0.09537 -0.0573 0.0062 1.0000
19.000 1.6074 0.10642 0.10174 -0.0591 0.0060 1.0000
19.250 1.5897 0.11275 0.10820 -0.0612 0.0060 1.0000
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