RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 200,000 Max Cl/Cd: 85.73 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32-il-200000.txt Download as CSV file: xf-raf32-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3296 0.09402 0.09060 -0.0724 0.9761 0.0782
-9.000 -0.3135 0.08916 0.08573 -0.0730 0.9740 0.0797
-8.750 -0.3912 0.05845 0.05487 -0.1018 0.9583 0.0553
-8.500 -0.4077 0.04971 0.04580 -0.1088 0.9466 0.0541
-8.250 -0.4128 0.04173 0.03719 -0.1137 0.9381 0.0539
-8.000 -0.4008 0.03650 0.03118 -0.1163 0.9315 0.0555
-7.750 -0.3736 0.03278 0.02704 -0.1194 0.9290 0.0582
-7.500 -0.3562 0.03199 0.02626 -0.1182 0.9220 0.0602
-7.250 -0.3296 0.03015 0.02412 -0.1192 0.9177 0.0629
-7.000 -0.2951 0.02880 0.02221 -0.1212 0.9150 0.0665
-6.750 -0.2615 0.02619 0.01948 -0.1237 0.9134 0.0701
-6.500 -0.2461 0.02554 0.01873 -0.1217 0.9051 0.0727
-6.250 -0.2124 0.02461 0.01753 -0.1230 0.9020 0.0770
-6.000 -0.1772 0.02295 0.01565 -0.1249 0.9000 0.0807
-5.750 -0.1382 0.02204 0.01469 -0.1273 0.8986 0.0853
-5.500 -0.1181 0.02155 0.01408 -0.1259 0.8915 0.0885
-5.250 -0.0850 0.02067 0.01303 -0.1270 0.8878 0.0925
-5.000 -0.0475 0.01966 0.01204 -0.1290 0.8857 0.0971
-4.750 -0.0087 0.01897 0.01128 -0.1311 0.8839 0.1024
-4.500 0.0300 0.01812 0.01037 -0.1332 0.8824 0.1070
-4.250 0.0456 0.01781 0.01011 -0.1309 0.8737 0.1111
-4.000 0.0807 0.01727 0.00952 -0.1322 0.8705 0.1181
-3.750 0.1173 0.01652 0.00883 -0.1339 0.8683 0.1266
-3.500 0.1551 0.01587 0.00824 -0.1358 0.8664 0.1417
-3.250 0.1699 0.01569 0.00816 -0.1333 0.8572 0.1635
-3.000 0.2034 0.01500 0.00782 -0.1345 0.8538 0.2471
-2.750 0.2406 0.01464 0.00754 -0.1363 0.8514 0.2992
-2.500 0.2601 0.01470 0.00762 -0.1346 0.8434 0.3267
-2.250 0.2919 0.01446 0.00743 -0.1353 0.8391 0.3554
-2.000 0.3277 0.01414 0.00716 -0.1367 0.8361 0.3836
-1.750 0.3495 0.01414 0.00721 -0.1355 0.8289 0.4080
-1.500 0.3790 0.01393 0.00708 -0.1356 0.8236 0.4383
-1.250 0.4132 0.01363 0.00689 -0.1366 0.8201 0.4812
-1.000 0.4338 0.01362 0.00704 -0.1351 0.8125 0.5271
-0.750 0.4623 0.01342 0.00697 -0.1349 0.8071 0.5794
-0.500 0.4952 0.01313 0.00680 -0.1355 0.8035 0.6309
-0.250 0.5125 0.01315 0.00699 -0.1333 0.7954 0.6741
0.000 0.5403 0.01293 0.00689 -0.1329 0.7904 0.7250
0.250 0.5720 0.01263 0.00673 -0.1331 0.7870 0.7840
0.500 0.5979 0.01251 0.00690 -0.1324 0.7792 0.8764
0.750 0.6587 0.01236 0.00671 -0.1393 0.7751 1.0000
1.000 0.6932 0.01233 0.00656 -0.1406 0.7712 1.0000
1.250 0.7110 0.01258 0.00679 -0.1387 0.7631 1.0000
1.500 0.7412 0.01260 0.00672 -0.1391 0.7580 1.0000
1.750 0.7678 0.01272 0.00679 -0.1389 0.7523 1.0000
2.000 0.7917 0.01286 0.00692 -0.1381 0.7455 1.0000
2.250 0.8237 0.01287 0.00685 -0.1388 0.7409 1.0000
2.500 0.8452 0.01308 0.00707 -0.1375 0.7336 1.0000
2.750 0.8729 0.01315 0.00712 -0.1374 0.7277 1.0000
3.000 0.9031 0.01323 0.00716 -0.1378 0.7226 1.0000
3.250 0.9241 0.01342 0.00738 -0.1364 0.7147 1.0000
3.500 0.9572 0.01337 0.00727 -0.1372 0.7088 1.0000
3.750 0.9766 0.01353 0.00747 -0.1355 0.6993 1.0000
4.000 1.0082 0.01347 0.00735 -0.1359 0.6918 1.0000
4.250 1.0291 0.01357 0.00749 -0.1344 0.6817 1.0000
4.500 1.0545 0.01363 0.00754 -0.1337 0.6724 1.0000
4.750 1.0819 0.01365 0.00753 -0.1334 0.6631 1.0000
5.000 1.1028 0.01377 0.00770 -0.1319 0.6523 1.0000
5.250 1.1272 0.01383 0.00774 -0.1309 0.6411 1.0000
5.500 1.1533 0.01389 0.00778 -0.1304 0.6304 1.0000
5.750 1.1723 0.01405 0.00801 -0.1285 0.6186 1.0000
6.000 1.1933 0.01418 0.00816 -0.1270 0.6063 1.0000
6.250 1.2146 0.01431 0.00830 -0.1255 0.5936 1.0000
6.500 1.2338 0.01444 0.00843 -0.1237 0.5793 1.0000
6.750 1.2500 0.01458 0.00861 -0.1212 0.5628 1.0000
7.000 1.2638 0.01475 0.00879 -0.1183 0.5440 1.0000
7.250 1.2766 0.01496 0.00898 -0.1153 0.5238 1.0000
7.500 1.2876 0.01522 0.00920 -0.1119 0.5026 1.0000
7.750 1.2942 0.01556 0.00951 -0.1078 0.4785 1.0000
8.000 1.2999 0.01603 0.00989 -0.1036 0.4520 1.0000
8.250 1.3038 0.01664 0.01038 -0.0993 0.4225 1.0000
8.500 1.3053 0.01742 0.01102 -0.0948 0.3886 1.0000
8.750 1.3035 0.01842 0.01184 -0.0900 0.3492 1.0000
9.000 1.2973 0.01973 0.01290 -0.0849 0.3020 1.0000
9.250 1.2878 0.02141 0.01428 -0.0798 0.2545 1.0000
9.500 1.2782 0.02334 0.01593 -0.0752 0.2100 1.0000
9.750 1.2694 0.02546 0.01775 -0.0710 0.1614 1.0000
10.000 1.2613 0.02772 0.01971 -0.0673 0.1225 1.0000
10.250 1.2582 0.02978 0.02163 -0.0643 0.1031 1.0000
10.500 1.2581 0.03173 0.02352 -0.0617 0.0920 1.0000
10.750 1.2566 0.03386 0.02561 -0.0593 0.0842 1.0000
11.000 1.2596 0.03572 0.02751 -0.0573 0.0777 1.0000
11.250 1.2584 0.03799 0.02978 -0.0551 0.0725 1.0000
11.500 1.2638 0.03977 0.03163 -0.0535 0.0676 1.0000
11.750 1.2647 0.04202 0.03383 -0.0517 0.0637 1.0000
12.000 1.2713 0.04384 0.03574 -0.0502 0.0600 1.0000
12.250 1.2787 0.04560 0.03754 -0.0490 0.0565 1.0000
12.500 1.2856 0.04748 0.03937 -0.0477 0.0536 1.0000
12.750 1.2967 0.04911 0.04108 -0.0464 0.0510 1.0000
13.000 1.3069 0.05074 0.04282 -0.0454 0.0486 1.0000
13.250 1.3171 0.05238 0.04448 -0.0444 0.0464 1.0000
13.500 1.3367 0.05369 0.04569 -0.0434 0.0439 1.0000
13.750 1.3440 0.05559 0.04778 -0.0425 0.0424 1.0000
14.000 1.3559 0.05730 0.04964 -0.0416 0.0409 1.0000
14.250 1.3663 0.05912 0.05157 -0.0408 0.0395 1.0000
14.500 1.3769 0.06090 0.05338 -0.0401 0.0381 1.0000
14.750 1.3987 0.06256 0.05503 -0.0395 0.0364 1.0000
15.000 1.3992 0.06517 0.05789 -0.0386 0.0355 1.0000
15.250 1.4031 0.06782 0.06076 -0.0379 0.0347 1.0000
15.500 1.4068 0.07058 0.06372 -0.0372 0.0339 1.0000
15.750 1.4097 0.07346 0.06680 -0.0367 0.0332 1.0000
16.000 1.4120 0.07639 0.06989 -0.0363 0.0325 1.0000
16.250 1.4117 0.07954 0.07319 -0.0361 0.0320 1.0000
16.500 1.4123 0.08261 0.07637 -0.0361 0.0314 1.0000
16.750 1.4196 0.08575 0.07955 -0.0360 0.0305 1.0000
17.000 1.4087 0.09062 0.08467 -0.0363 0.0303 1.0000
17.250 1.3910 0.09583 0.09016 -0.0373 0.0301 1.0000
17.500 1.3726 0.10142 0.09603 -0.0388 0.0300 1.0000
17.750 1.3544 0.10741 0.10227 -0.0408 0.0299 1.0000
18.000 1.3338 0.11401 0.10912 -0.0435 0.0298 1.0000
18.250 1.3132 0.12104 0.11639 -0.0467 0.0298 1.0000
18.500 1.2913 0.12864 0.12421 -0.0507 0.0299 1.0000
18.750 1.2687 0.13679 0.13257 -0.0553 0.0300 1.0000
19.000 1.2451 0.14563 0.14159 -0.0608 0.0301 1.0000
19.250 1.2219 0.15497 0.15109 -0.0667 0.0303 1.0000
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