S4022 (s4022-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 200,000 Max Cl/Cd: 90.32 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4022-il-200000-n5.txt Download as CSV file: xf-s4022-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4022
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2746 0.09070 0.08725 -0.0625 0.9806 0.0281
-8.250 -0.2651 0.08654 0.08310 -0.0668 0.9757 0.0305
-8.000 -0.2659 0.07816 0.07473 -0.0739 0.9683 0.0229
-7.750 -0.2585 0.07393 0.07052 -0.0775 0.9626 0.0218
-7.500 -0.2578 0.06913 0.06575 -0.0814 0.9536 0.0209
-7.250 -0.2507 0.05829 0.05489 -0.0964 0.9435 0.0194
-7.000 -0.2397 0.04108 0.03677 -0.1162 0.9342 0.0168
-6.750 -0.2249 0.03680 0.03210 -0.1187 0.9256 0.0168
-6.500 -0.1962 0.03233 0.02712 -0.1231 0.9225 0.0168
-6.250 -0.1638 0.02801 0.02225 -0.1273 0.9206 0.0171
-6.000 -0.1415 0.02550 0.01938 -0.1279 0.9136 0.0174
-5.750 -0.1093 0.02373 0.01739 -0.1300 0.9107 0.0184
-5.500 -0.0745 0.02240 0.01586 -0.1323 0.9085 0.0199
-5.250 -0.0377 0.02059 0.01369 -0.1346 0.9069 0.0202
-5.000 -0.0128 0.01933 0.01221 -0.1343 0.9001 0.0203
-4.750 0.0213 0.01803 0.01073 -0.1357 0.8970 0.0206
-4.500 0.0579 0.01690 0.00946 -0.1377 0.8947 0.0210
-4.250 0.0929 0.01597 0.00843 -0.1394 0.8915 0.0216
-4.000 0.1224 0.01527 0.00763 -0.1400 0.8856 0.0224
-3.750 0.1595 0.01458 0.00685 -0.1421 0.8822 0.0233
-3.500 0.1990 0.01386 0.00602 -0.1448 0.8795 0.0254
-3.250 0.2279 0.01349 0.00561 -0.1453 0.8727 0.0291
-3.000 0.2637 0.01310 0.00509 -0.1470 0.8682 0.0324
-2.750 0.3010 0.01265 0.00462 -0.1491 0.8641 0.0435
-2.500 0.3322 0.01200 0.00432 -0.1504 0.8572 0.1417
-2.250 0.3705 0.01106 0.00409 -0.1535 0.8527 0.3473
-2.000 0.4010 0.01070 0.00415 -0.1543 0.8458 0.4864
-1.750 0.4328 0.01062 0.00424 -0.1550 0.8397 0.5768
-1.500 0.4622 0.01063 0.00426 -0.1552 0.8326 0.6110
-1.250 0.4932 0.01062 0.00419 -0.1557 0.8257 0.6294
-1.000 0.5221 0.01063 0.00415 -0.1558 0.8181 0.6444
-0.750 0.5526 0.01063 0.00410 -0.1562 0.8109 0.6576
-0.500 0.5802 0.01065 0.00410 -0.1561 0.8026 0.6694
-0.250 0.6109 0.01066 0.00405 -0.1566 0.7956 0.6805
0.000 0.6376 0.01070 0.00407 -0.1563 0.7867 0.6910
0.250 0.6667 0.01073 0.00406 -0.1565 0.7790 0.7006
0.500 0.6939 0.01076 0.00409 -0.1563 0.7701 0.7097
0.750 0.7213 0.01081 0.00412 -0.1561 0.7615 0.7195
1.000 0.7496 0.01085 0.00413 -0.1562 0.7531 0.7288
1.250 0.7753 0.01091 0.00421 -0.1557 0.7433 0.7381
1.500 0.8023 0.01097 0.00427 -0.1555 0.7340 0.7481
2.000 0.8546 0.01109 0.00443 -0.1546 0.7140 0.7680
2.250 0.8802 0.01117 0.00452 -0.1541 0.7033 0.7789
2.500 0.9059 0.01125 0.00461 -0.1536 0.6924 0.7907
2.750 0.9309 0.01133 0.00471 -0.1529 0.6809 0.8030
3.000 0.9552 0.01142 0.00484 -0.1521 0.6686 0.8166
3.250 0.9786 0.01152 0.00496 -0.1511 0.6552 0.8318
3.500 1.0011 0.01161 0.00508 -0.1499 0.6415 0.8492
3.750 1.0224 0.01170 0.00520 -0.1484 0.6275 0.8712
4.250 1.0635 0.01180 0.00538 -0.1451 0.5957 1.0000
4.500 1.0883 0.01205 0.00559 -0.1446 0.5771 1.0000
4.750 1.1123 0.01233 0.00581 -0.1440 0.5583 1.0000
5.000 1.1354 0.01264 0.00606 -0.1431 0.5380 1.0000
5.250 1.1573 0.01297 0.00633 -0.1421 0.5153 1.0000
5.500 1.1782 0.01335 0.00667 -0.1408 0.4909 1.0000
5.750 1.1979 0.01377 0.00701 -0.1394 0.4650 1.0000
6.000 1.2164 0.01423 0.00739 -0.1377 0.4375 1.0000
6.250 1.2339 0.01474 0.00781 -0.1359 0.4089 1.0000
6.500 1.2498 0.01532 0.00827 -0.1338 0.3777 1.0000
6.750 1.2637 0.01594 0.00877 -0.1314 0.3457 1.0000
7.000 1.2762 0.01664 0.00937 -0.1288 0.3135 1.0000
7.250 1.2884 0.01739 0.01000 -0.1263 0.2806 1.0000
7.500 1.2996 0.01824 0.01071 -0.1236 0.2471 1.0000
7.750 1.3103 0.01915 0.01149 -0.1210 0.2163 1.0000
8.000 1.3217 0.02006 0.01230 -0.1185 0.1887 1.0000
8.250 1.3319 0.02108 0.01320 -0.1160 0.1613 1.0000
8.500 1.3406 0.02222 0.01419 -0.1134 0.1333 1.0000
8.750 1.3492 0.02340 0.01524 -0.1108 0.1082 1.0000
9.000 1.3589 0.02453 0.01633 -0.1085 0.0889 1.0000
9.250 1.3694 0.02563 0.01741 -0.1064 0.0756 1.0000
9.500 1.3794 0.02679 0.01855 -0.1043 0.0637 1.0000
9.750 1.3894 0.02797 0.01975 -0.1022 0.0543 1.0000
10.000 1.3985 0.02925 0.02104 -0.1002 0.0455 1.0000
10.250 1.4069 0.03064 0.02244 -0.0982 0.0359 1.0000
10.500 1.4137 0.03219 0.02399 -0.0961 0.0266 1.0000
10.750 1.4193 0.03390 0.02572 -0.0940 0.0195 1.0000
11.000 1.4247 0.03569 0.02760 -0.0920 0.0161 1.0000
11.250 1.4295 0.03757 0.02960 -0.0901 0.0140 1.0000
11.500 1.4322 0.03973 0.03187 -0.0882 0.0127 1.0000
11.750 1.4356 0.04188 0.03417 -0.0865 0.0119 1.0000
12.000 1.4386 0.04413 0.03658 -0.0850 0.0113 1.0000
12.250 1.4407 0.04655 0.03916 -0.0836 0.0108 1.0000
12.500 1.4422 0.04910 0.04187 -0.0824 0.0103 1.0000
12.750 1.4432 0.05179 0.04470 -0.0813 0.0097 1.0000
13.000 1.4433 0.05467 0.04772 -0.0805 0.0092 1.0000
13.250 1.4408 0.05799 0.05117 -0.0799 0.0088 1.0000
13.500 1.4345 0.06190 0.05523 -0.0794 0.0084 1.0000
13.750 1.4317 0.06553 0.05901 -0.0792 0.0081 1.0000
14.000 1.4299 0.06914 0.06281 -0.0791 0.0079 1.0000
14.250 1.4268 0.07307 0.06691 -0.0793 0.0078 1.0000
14.500 1.4232 0.07718 0.07120 -0.0797 0.0076 1.0000
14.750 1.4191 0.08150 0.07570 -0.0803 0.0075 1.0000
15.000 1.4147 0.08600 0.08042 -0.0812 0.0073 1.0000
15.250 1.4097 0.09072 0.08532 -0.0823 0.0072 1.0000
15.500 1.4042 0.09560 0.09038 -0.0837 0.0071 1.0000
15.750 1.3982 0.10072 0.09568 -0.0853 0.0070 1.0000
16.000 1.3919 0.10602 0.10118 -0.0873 0.0069 1.0000
16.250 1.3849 0.11157 0.10692 -0.0895 0.0068 1.0000
16.500 1.3772 0.11739 0.11292 -0.0921 0.0067 1.0000
16.750 1.3691 0.12342 0.11914 -0.0951 0.0067 1.0000
17.000 1.3606 0.12969 0.12560 -0.0983 0.0066 1.0000
17.250 1.3513 0.13632 0.13241 -0.1021 0.0066 1.0000
17.500 1.3413 0.14330 0.13958 -0.1063 0.0066 1.0000
17.750 1.3308 0.15061 0.14708 -0.1108 0.0065 1.0000
18.000 1.3195 0.15839 0.15504 -0.1159 0.0065 1.0000
18.250 1.3072 0.16673 0.16356 -0.1215 0.0066 1.0000
18.500 1.2935 0.17591 0.17292 -0.1278 0.0066 1.0000
18.750 1.2782 0.18603 0.18320 -0.1348 0.0067 1.0000
19.000 1.2592 0.19811 0.19544 -0.1429 0.0068 1.0000
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Polar data table (+)
Polar graphs
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