Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 200,000 Max Cl/Cd: 52.21 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371i-il-200000-n5.txt Download as CSV file: xf-supermarine371i-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-I (root)
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6931 0.08062 0.07681 -0.0465 1.0000 0.0192
-13.000 -0.7533 0.06584 0.06170 -0.0568 1.0000 0.0185
-12.750 -0.7826 0.05920 0.05485 -0.0599 1.0000 0.0185
-12.500 -0.8128 0.05330 0.04866 -0.0611 1.0000 0.0183
-12.250 -0.8192 0.05071 0.04595 -0.0609 1.0000 0.0187
-12.000 -0.8328 0.04744 0.04247 -0.0601 1.0000 0.0188
-11.750 -0.8437 0.04458 0.03938 -0.0586 1.0000 0.0190
-11.500 -0.8517 0.04212 0.03671 -0.0566 1.0000 0.0193
-11.250 -0.8580 0.03978 0.03413 -0.0541 1.0000 0.0195
-11.000 -0.8621 0.03775 0.03187 -0.0511 1.0000 0.0199
-10.750 -0.8637 0.03586 0.02975 -0.0481 1.0000 0.0201
-10.500 -0.8461 0.03344 0.02697 -0.0486 0.9674 0.0207
-10.250 -0.8231 0.03131 0.02447 -0.0497 0.9507 0.0211
-10.000 -0.8006 0.02954 0.02244 -0.0503 0.9368 0.0220
-9.750 -0.7789 0.02830 0.02109 -0.0504 0.9245 0.0227
-9.500 -0.7585 0.02724 0.01988 -0.0500 0.9136 0.0235
-9.250 -0.7384 0.02616 0.01865 -0.0493 0.9039 0.0241
-9.000 -0.7179 0.02508 0.01742 -0.0485 0.8958 0.0249
-8.750 -0.6973 0.02408 0.01627 -0.0477 0.8886 0.0257
-8.500 -0.6764 0.02313 0.01519 -0.0469 0.8820 0.0264
-8.250 -0.6556 0.02233 0.01422 -0.0460 0.8757 0.0273
-8.000 -0.6366 0.02142 0.01325 -0.0450 0.8703 0.0286
-7.750 -0.6170 0.02075 0.01255 -0.0441 0.8643 0.0300
-7.500 -0.5971 0.02012 0.01185 -0.0430 0.8590 0.0315
-7.250 -0.5771 0.01950 0.01113 -0.0419 0.8543 0.0331
-7.000 -0.5565 0.01892 0.01044 -0.0409 0.8491 0.0347
-6.750 -0.5377 0.01821 0.00968 -0.0396 0.8445 0.0367
-6.500 -0.5176 0.01765 0.00905 -0.0385 0.8410 0.0395
-6.250 -0.4959 0.01719 0.00851 -0.0377 0.8369 0.0432
-6.000 -0.4754 0.01663 0.00790 -0.0367 0.8328 0.0476
-5.750 -0.4543 0.01613 0.00734 -0.0357 0.8293 0.0533
-5.500 -0.4334 0.01563 0.00687 -0.0347 0.8263 0.0622
-5.250 -0.4103 0.01530 0.00672 -0.0342 0.8231 0.0942
-5.000 -0.3856 0.01512 0.00647 -0.0338 0.8195 0.1102
-4.750 -0.3626 0.01480 0.00615 -0.0331 0.8161 0.1208
-4.500 -0.3389 0.01453 0.00585 -0.0326 0.8131 0.1301
-4.250 -0.3150 0.01428 0.00557 -0.0320 0.8108 0.1386
-4.000 -0.2912 0.01401 0.00532 -0.0315 0.8083 0.1494
-3.750 -0.2677 0.01372 0.00512 -0.0310 0.8052 0.1681
-3.500 -0.2455 0.01333 0.00491 -0.0304 0.8024 0.2117
-3.250 -0.2256 0.01277 0.00467 -0.0293 0.7997 0.2885
-3.000 -0.2067 0.01217 0.00442 -0.0280 0.7971 0.3804
-2.750 -0.1886 0.01157 0.00424 -0.0264 0.7948 0.4803
-2.500 -0.1708 0.01120 0.00444 -0.0244 0.7922 0.5916
-2.250 -0.1462 0.01123 0.00455 -0.0237 0.7896 0.6571
-2.000 -0.1202 0.01128 0.00461 -0.0233 0.7872 0.6794
-1.750 -0.0939 0.01133 0.00465 -0.0229 0.7849 0.6970
-1.500 -0.0676 0.01140 0.00470 -0.0225 0.7827 0.7135
-1.250 -0.0410 0.01146 0.00475 -0.0221 0.7807 0.7282
-1.000 -0.0138 0.01153 0.00480 -0.0219 0.7791 0.7382
-0.750 0.0126 0.01162 0.00490 -0.0217 0.7768 0.7482
-0.500 0.0389 0.01171 0.00500 -0.0214 0.7742 0.7575
-0.250 0.0656 0.01177 0.00508 -0.0213 0.7715 0.7644
0.000 0.0928 0.01183 0.00514 -0.0212 0.7692 0.7700
0.250 0.1197 0.01188 0.00518 -0.0211 0.7671 0.7769
0.500 0.1475 0.01191 0.00521 -0.0209 0.7646 0.7822
0.750 0.1740 0.01194 0.00527 -0.0207 0.7606 0.7869
1.000 0.2002 0.01198 0.00531 -0.0205 0.7561 0.7918
1.250 0.2276 0.01200 0.00537 -0.0204 0.7529 0.7954
1.500 0.2554 0.01200 0.00539 -0.0204 0.7499 0.7999
1.750 0.2817 0.01200 0.00542 -0.0201 0.7445 0.8050
2.000 0.3080 0.01195 0.00541 -0.0197 0.7378 0.8097
2.250 0.3361 0.01189 0.00537 -0.0195 0.7333 0.8146
2.500 0.3610 0.01191 0.00547 -0.0189 0.7263 0.8208
2.750 0.3883 0.01180 0.00538 -0.0186 0.7191 0.8259
3.000 0.4136 0.01177 0.00545 -0.0180 0.7107 0.8313
3.250 0.4407 0.01163 0.00532 -0.0175 0.7017 0.8376
3.500 0.4657 0.01152 0.00528 -0.0167 0.6883 0.8430
3.750 0.4907 0.01146 0.00532 -0.0160 0.6754 0.8487
4.000 0.5158 0.01142 0.00534 -0.0154 0.6618 0.8547
4.250 0.5411 0.01132 0.00529 -0.0147 0.6422 0.8586
4.500 0.5649 0.01126 0.00528 -0.0138 0.6111 0.8634
4.750 0.5874 0.01125 0.00510 -0.0125 0.5502 0.8691
5.000 0.6025 0.01168 0.00510 -0.0099 0.4691 0.8746
5.250 0.6148 0.01235 0.00542 -0.0073 0.3945 0.8821
5.500 0.6274 0.01307 0.00585 -0.0048 0.3287 0.8899
6.000 0.6562 0.01449 0.00680 -0.0010 0.2151 0.9098
6.250 0.6740 0.01517 0.00730 0.0002 0.1718 0.9213
6.500 0.6951 0.01585 0.00783 0.0007 0.1359 0.9339
6.750 0.7204 0.01653 0.00841 0.0003 0.1099 0.9471
7.000 0.7486 0.01726 0.00906 -0.0008 0.0886 0.9610
7.250 0.7790 0.01794 0.00971 -0.0023 0.0727 0.9775
7.500 0.8061 0.01866 0.01040 -0.0033 0.0615 1.0000
7.750 0.8155 0.01915 0.01087 -0.0005 0.0553 1.0000
8.000 0.8260 0.01976 0.01147 0.0021 0.0500 1.0000
8.250 0.8389 0.02035 0.01210 0.0041 0.0452 1.0000
8.500 0.8502 0.02113 0.01284 0.0062 0.0412 1.0000
8.750 0.8642 0.02181 0.01359 0.0079 0.0384 1.0000
9.000 0.8776 0.02258 0.01441 0.0096 0.0358 1.0000
9.250 0.8896 0.02348 0.01533 0.0113 0.0337 1.0000
9.500 0.9013 0.02448 0.01637 0.0130 0.0321 1.0000
9.750 0.9156 0.02534 0.01732 0.0144 0.0303 1.0000
10.000 0.9295 0.02623 0.01827 0.0158 0.0285 1.0000
10.250 0.9427 0.02719 0.01928 0.0171 0.0273 1.0000
10.500 0.9540 0.02836 0.02047 0.0185 0.0262 1.0000
10.750 0.9652 0.02969 0.02186 0.0200 0.0253 1.0000
11.000 0.9789 0.03081 0.02312 0.0211 0.0244 1.0000
11.250 0.9921 0.03195 0.02438 0.0223 0.0233 1.0000
11.500 1.0041 0.03318 0.02571 0.0234 0.0223 1.0000
11.750 1.0152 0.03441 0.02703 0.0245 0.0215 1.0000
12.000 1.0253 0.03580 0.02849 0.0256 0.0209 1.0000
12.250 1.0340 0.03737 0.03013 0.0267 0.0202 1.0000
12.500 1.0419 0.03927 0.03214 0.0279 0.0197 1.0000
12.750 1.0497 0.04100 0.03407 0.0289 0.0192 1.0000
13.000 1.0553 0.04301 0.03629 0.0300 0.0187 1.0000
13.250 1.0588 0.04511 0.03860 0.0310 0.0180 1.0000
13.500 1.0607 0.04736 0.04102 0.0318 0.0175 1.0000
13.750 1.0614 0.04968 0.04351 0.0325 0.0170 1.0000
14.000 1.0618 0.05199 0.04595 0.0329 0.0165 1.0000
14.250 1.0599 0.05473 0.04883 0.0332 0.0163 1.0000
14.500 1.0560 0.05781 0.05206 0.0333 0.0160 1.0000
14.750 1.0504 0.06118 0.05559 0.0330 0.0159 1.0000
15.000 1.0437 0.06484 0.05938 0.0324 0.0157 1.0000
15.250 1.0358 0.06885 0.06353 0.0314 0.0155 1.0000
15.500 1.0233 0.07386 0.06873 0.0297 0.0154 1.0000
16.000 0.9916 0.08605 0.08130 0.0241 0.0152 1.0000
16.250 0.9710 0.09381 0.08926 0.0197 0.0152 1.0000
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