S2055 (s2055-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 500,000 Max Cl/Cd: 92.85 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2055-il-500000.txt Download as CSV file: xf-s2055-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S2055
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4931 0.07598 0.07381 -0.0349 1.0000 0.0153
-8.250 -0.5013 0.07191 0.06977 -0.0380 1.0000 0.0152
-8.000 -0.5082 0.06797 0.06581 -0.0393 1.0000 0.0151
-7.750 -0.5277 0.06224 0.06004 -0.0397 1.0000 0.0155
-7.500 -0.5353 0.05831 0.05604 -0.0389 1.0000 0.0156
-7.250 -0.5397 0.05560 0.05329 -0.0371 1.0000 0.0159
-7.000 -0.5420 0.05240 0.05001 -0.0355 1.0000 0.0161
-6.750 -0.5414 0.04994 0.04748 -0.0336 1.0000 0.0165
-6.500 -0.5389 0.04763 0.04509 -0.0317 1.0000 0.0171
-6.250 -0.5198 0.04354 0.04080 -0.0335 0.9981 0.0180
-6.000 -0.4898 0.03890 0.03585 -0.0365 0.9952 0.0206
-5.750 -0.4542 0.03718 0.03371 -0.0378 0.9925 0.0223
-5.500 -0.4381 0.02839 0.02435 -0.0401 0.9879 0.0240
-5.250 -0.4074 0.02592 0.02171 -0.0418 0.9855 0.0250
-5.000 -0.3775 0.01770 0.01237 -0.0406 0.9837 0.0134
-4.750 -0.3479 0.01569 0.01004 -0.0408 0.9806 0.0137
-4.500 -0.3167 0.01443 0.00857 -0.0414 0.9772 0.0144
-4.250 -0.2848 0.01286 0.00680 -0.0423 0.9747 0.0158
-4.000 -0.2505 0.01204 0.00597 -0.0439 0.9727 0.0189
-3.750 -0.2142 0.01145 0.00531 -0.0457 0.9711 0.0218
-3.500 -0.1842 0.01051 0.00428 -0.0462 0.9672 0.0264
-3.250 -0.1516 0.01020 0.00395 -0.0472 0.9633 0.0322
-3.000 -0.1166 0.00957 0.00336 -0.0488 0.9608 0.0507
-2.750 -0.0816 0.00900 0.00303 -0.0505 0.9586 0.1102
-2.500 -0.0474 0.00840 0.00277 -0.0522 0.9565 0.2052
-2.250 -0.0240 0.00768 0.00258 -0.0517 0.9488 0.3552
-2.000 0.0033 0.00675 0.00238 -0.0519 0.9444 0.5641
-1.750 0.0238 0.00606 0.00236 -0.0501 0.9369 0.7515
-1.500 0.0496 0.00583 0.00231 -0.0490 0.9304 0.8296
-1.250 0.0737 0.00572 0.00224 -0.0476 0.9209 0.8629
-1.000 0.0988 0.00563 0.00214 -0.0464 0.9112 0.8877
-0.750 0.1238 0.00556 0.00204 -0.0452 0.9003 0.9050
-0.500 0.1473 0.00553 0.00197 -0.0437 0.8879 0.9235
-0.250 0.1701 0.00555 0.00196 -0.0419 0.8759 0.9435
0.000 0.1979 0.00558 0.00195 -0.0414 0.8651 0.9579
0.250 0.2321 0.00562 0.00194 -0.0424 0.8549 0.9683
0.500 0.2725 0.00566 0.00191 -0.0449 0.8450 0.9741
0.750 0.3133 0.00569 0.00190 -0.0476 0.8333 0.9789
1.000 0.3516 0.00573 0.00188 -0.0498 0.8202 0.9841
1.250 0.3921 0.00575 0.00186 -0.0525 0.8064 0.9877
1.500 0.4292 0.00579 0.00184 -0.0545 0.7907 0.9922
1.750 0.4657 0.00582 0.00183 -0.0564 0.7738 0.9960
2.000 0.5025 0.00585 0.00182 -0.0584 0.7527 0.9997
2.250 0.5253 0.00590 0.00181 -0.0574 0.7309 1.0000
2.500 0.5462 0.00598 0.00182 -0.0560 0.7044 1.0000
2.750 0.5664 0.00610 0.00184 -0.0544 0.6708 1.0000
3.000 0.5845 0.00633 0.00187 -0.0524 0.6180 1.0000
3.250 0.5994 0.00677 0.00197 -0.0499 0.5359 1.0000
3.500 0.6144 0.00730 0.00214 -0.0475 0.4551 1.0000
3.750 0.6317 0.00776 0.00234 -0.0456 0.3941 1.0000
4.000 0.6511 0.00814 0.00255 -0.0441 0.3495 1.0000
4.250 0.6715 0.00852 0.00276 -0.0428 0.3110 1.0000
4.500 0.6928 0.00889 0.00301 -0.0416 0.2751 1.0000
4.750 0.7149 0.00927 0.00325 -0.0407 0.2428 1.0000
5.000 0.7378 0.00963 0.00350 -0.0399 0.2123 1.0000
5.250 0.7611 0.00998 0.00377 -0.0392 0.1863 1.0000
5.500 0.7843 0.01038 0.00407 -0.0385 0.1538 1.0000
5.750 0.8058 0.01100 0.00444 -0.0376 0.1059 1.0000
6.000 0.8269 0.01169 0.00493 -0.0366 0.0695 1.0000
6.250 0.8491 0.01229 0.00546 -0.0357 0.0497 1.0000
6.500 0.8710 0.01298 0.00610 -0.0348 0.0366 1.0000
6.750 0.8931 0.01363 0.00683 -0.0338 0.0301 1.0000
7.000 0.9155 0.01424 0.00747 -0.0329 0.0261 1.0000
7.250 0.9340 0.01535 0.00868 -0.0314 0.0230 1.0000
7.500 0.9574 0.01581 0.00921 -0.0307 0.0210 1.0000
7.750 0.9791 0.01648 0.00995 -0.0297 0.0192 1.0000
8.000 0.9989 0.01737 0.01089 -0.0286 0.0171 1.0000
8.250 1.0152 0.01884 0.01251 -0.0269 0.0153 1.0000
8.500 1.0364 0.01960 0.01339 -0.0259 0.0141 1.0000
8.750 1.0565 0.02047 0.01436 -0.0248 0.0128 1.0000
9.000 1.0755 0.02141 0.01537 -0.0236 0.0117 1.0000
9.250 1.0852 0.02441 0.01860 -0.0212 0.0105 1.0000
9.500 1.0998 0.02647 0.02092 -0.0195 0.0101 1.0000
9.750 1.1169 0.02756 0.02220 -0.0181 0.0095 1.0000
10.000 1.1322 0.02880 0.02361 -0.0165 0.0089 1.0000
10.250 1.1459 0.03002 0.02498 -0.0149 0.0082 1.0000
10.500 1.1557 0.03171 0.02686 -0.0129 0.0079 1.0000
10.750 1.1649 0.03292 0.02821 -0.0108 0.0075 1.0000
11.000 1.1643 0.03512 0.03064 -0.0075 0.0074 1.0000
11.250 1.1620 0.03713 0.03283 -0.0044 0.0072 1.0000
11.500 1.1555 0.03955 0.03544 -0.0014 0.0071 1.0000
11.750 1.1435 0.04262 0.03873 0.0014 0.0070 1.0000
12.000 1.1297 0.04604 0.04238 0.0033 0.0069 1.0000
12.250 1.1097 0.05045 0.04702 0.0042 0.0068 1.0000
12.500 1.1002 0.05410 0.05089 0.0040 0.0071 1.0000
12.750 1.0750 0.06025 0.05722 0.0020 0.0068 1.0000
13.000 1.0594 0.06601 0.06316 -0.0011 0.0069 1.0000
13.250 1.0421 0.07302 0.07034 -0.0057 0.0069 1.0000
13.500 1.0241 0.08138 0.07887 -0.0116 0.0069 1.0000
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Polar data table (+)
Polar graphs
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