RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 200,000 Max Cl/Cd: 62.68 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a111-il-200000-n5.txt Download as CSV file: xf-rg15a111-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A-1.8/11.0 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5286 0.09851 0.09475 -0.0311 1.0000 0.0148
-11.250 -0.6870 0.05531 0.05111 -0.0597 1.0000 0.0129
-11.000 -0.7068 0.05042 0.04607 -0.0622 1.0000 0.0128
-10.750 -0.7274 0.04665 0.04212 -0.0623 1.0000 0.0128
-10.500 -0.7490 0.04395 0.03925 -0.0597 1.0000 0.0129
-10.250 -0.7634 0.04122 0.03627 -0.0567 1.0000 0.0129
-10.000 -0.7726 0.03831 0.03312 -0.0540 1.0000 0.0131
-9.750 -0.7736 0.03596 0.03059 -0.0516 1.0000 0.0133
-9.500 -0.7696 0.03402 0.02848 -0.0494 1.0000 0.0136
-9.250 -0.7626 0.03228 0.02656 -0.0473 1.0000 0.0139
-9.000 -0.7539 0.03054 0.02462 -0.0453 1.0000 0.0143
-8.750 -0.7433 0.02896 0.02282 -0.0433 1.0000 0.0148
-8.500 -0.7309 0.02751 0.02115 -0.0414 1.0000 0.0155
-8.250 -0.7170 0.02619 0.01959 -0.0396 1.0000 0.0165
-8.000 -0.7015 0.02509 0.01818 -0.0379 1.0000 0.0174
-7.750 -0.6876 0.02344 0.01644 -0.0361 1.0000 0.0181
-7.500 -0.6668 0.02231 0.01522 -0.0355 0.9991 0.0190
-7.250 -0.6352 0.02120 0.01398 -0.0370 0.9958 0.0201
-7.000 -0.6035 0.02022 0.01285 -0.0383 0.9925 0.0217
-6.750 -0.5727 0.01924 0.01172 -0.0394 0.9885 0.0235
-6.500 -0.5407 0.01829 0.01072 -0.0409 0.9849 0.0253
-6.250 -0.5090 0.01754 0.00989 -0.0421 0.9809 0.0272
-6.000 -0.4782 0.01692 0.00916 -0.0430 0.9758 0.0298
-5.750 -0.4454 0.01616 0.00838 -0.0445 0.9718 0.0333
-5.500 -0.4148 0.01557 0.00770 -0.0452 0.9665 0.0375
-5.250 -0.3835 0.01494 0.00708 -0.0462 0.9611 0.0449
-5.000 -0.3489 0.01439 0.00654 -0.0479 0.9575 0.0599
-4.750 -0.3200 0.01391 0.00611 -0.0483 0.9505 0.0776
-4.500 -0.2864 0.01346 0.00569 -0.0497 0.9457 0.0975
-4.250 -0.2528 0.01301 0.00533 -0.0511 0.9410 0.1229
-4.000 -0.2227 0.01253 0.00501 -0.0518 0.9338 0.1626
-3.750 -0.1876 0.01200 0.00467 -0.0536 0.9292 0.2124
-3.500 -0.1586 0.01158 0.00440 -0.0540 0.9207 0.2601
-3.250 -0.1244 0.01111 0.00411 -0.0555 0.9149 0.3156
-3.000 -0.0955 0.01069 0.00389 -0.0558 0.9055 0.3757
-2.750 -0.0629 0.01020 0.00367 -0.0569 0.8986 0.4538
-2.500 -0.0350 0.00981 0.00359 -0.0568 0.8883 0.5359
-2.250 -0.0057 0.00960 0.00357 -0.0568 0.8783 0.6043
-2.000 0.0257 0.00949 0.00349 -0.0572 0.8684 0.6468
-1.750 0.0555 0.00943 0.00342 -0.0573 0.8569 0.6760
-1.500 0.0842 0.00938 0.00337 -0.0571 0.8444 0.6990
-1.250 0.1129 0.00935 0.00330 -0.0569 0.8316 0.7193
-1.000 0.1411 0.00934 0.00325 -0.0566 0.8184 0.7366
-0.750 0.1687 0.00933 0.00322 -0.0563 0.8047 0.7522
-0.500 0.1960 0.00934 0.00318 -0.0558 0.7904 0.7667
-0.250 0.2230 0.00935 0.00315 -0.0553 0.7755 0.7804
0.000 0.2494 0.00937 0.00313 -0.0547 0.7601 0.7933
0.250 0.2755 0.00940 0.00313 -0.0540 0.7443 0.8059
0.500 0.3012 0.00944 0.00313 -0.0532 0.7283 0.8182
0.750 0.3268 0.00948 0.00313 -0.0525 0.7118 0.8304
1.000 0.3521 0.00954 0.00314 -0.0517 0.6951 0.8425
1.250 0.3773 0.00960 0.00316 -0.0508 0.6780 0.8547
1.500 0.4020 0.00965 0.00319 -0.0499 0.6599 0.8665
1.750 0.4266 0.00972 0.00323 -0.0490 0.6412 0.8786
2.000 0.4515 0.00981 0.00326 -0.0481 0.6222 0.8907
2.250 0.4770 0.00990 0.00331 -0.0475 0.6025 0.9029
2.500 0.5034 0.01000 0.00337 -0.0470 0.5815 0.9157
2.750 0.5309 0.01014 0.00344 -0.0468 0.5598 0.9293
3.000 0.5607 0.01028 0.00353 -0.0472 0.5366 0.9436
3.250 0.5928 0.01046 0.00363 -0.0481 0.5128 0.9585
3.500 0.6262 0.01067 0.00377 -0.0495 0.4881 0.9748
3.750 0.6601 0.01089 0.00391 -0.0510 0.4626 0.9961
4.000 0.6837 0.01114 0.00408 -0.0503 0.4401 1.0000
4.250 0.7061 0.01141 0.00427 -0.0494 0.4168 1.0000
4.500 0.7289 0.01171 0.00448 -0.0486 0.3928 1.0000
4.750 0.7515 0.01203 0.00471 -0.0477 0.3681 1.0000
5.000 0.7743 0.01237 0.00496 -0.0469 0.3434 1.0000
5.250 0.7973 0.01272 0.00525 -0.0462 0.3200 1.0000
5.500 0.8200 0.01310 0.00555 -0.0454 0.2973 1.0000
5.750 0.8429 0.01348 0.00588 -0.0446 0.2748 1.0000
6.250 0.8880 0.01432 0.00662 -0.0431 0.2323 1.0000
6.500 0.9097 0.01481 0.00703 -0.0422 0.2101 1.0000
6.750 0.9313 0.01532 0.00747 -0.0413 0.1869 1.0000
7.000 0.9523 0.01587 0.00794 -0.0404 0.1649 1.0000
7.250 0.9733 0.01643 0.00844 -0.0395 0.1455 1.0000
7.500 0.9939 0.01701 0.00899 -0.0385 0.1288 1.0000
7.750 1.0142 0.01761 0.00956 -0.0375 0.1141 1.0000
8.000 1.0345 0.01821 0.01015 -0.0364 0.1014 1.0000
8.250 1.0542 0.01884 0.01078 -0.0353 0.0896 1.0000
8.500 1.0734 0.01949 0.01145 -0.0342 0.0793 1.0000
8.750 1.0917 0.02018 0.01219 -0.0329 0.0708 1.0000
9.000 1.1085 0.02098 0.01298 -0.0314 0.0629 1.0000
9.250 1.1262 0.02167 0.01375 -0.0301 0.0565 1.0000
9.500 1.1405 0.02257 0.01464 -0.0283 0.0509 1.0000
9.750 1.1556 0.02330 0.01551 -0.0265 0.0467 1.0000
10.000 1.1678 0.02417 0.01642 -0.0244 0.0430 1.0000
10.250 1.1780 0.02517 0.01746 -0.0221 0.0398 1.0000
10.500 1.1905 0.02603 0.01847 -0.0203 0.0367 1.0000
10.750 1.2008 0.02704 0.01953 -0.0183 0.0337 1.0000
11.000 1.2089 0.02821 0.02075 -0.0162 0.0309 1.0000
11.250 1.2198 0.02922 0.02189 -0.0145 0.0282 1.0000
11.500 1.2281 0.03043 0.02319 -0.0128 0.0260 1.0000
11.750 1.2307 0.03209 0.02490 -0.0108 0.0241 1.0000
12.000 1.2381 0.03348 0.02645 -0.0093 0.0226 1.0000
12.250 1.2445 0.03501 0.02812 -0.0079 0.0207 1.0000
12.500 1.2482 0.03681 0.03006 -0.0067 0.0194 1.0000
12.750 1.2478 0.03907 0.03242 -0.0056 0.0184 1.0000
13.000 1.2465 0.04157 0.03505 -0.0047 0.0174 1.0000
13.250 1.2468 0.04408 0.03774 -0.0042 0.0164 1.0000
13.500 1.2459 0.04684 0.04065 -0.0040 0.0154 1.0000
13.750 1.2435 0.04990 0.04385 -0.0042 0.0147 1.0000
14.000 1.2397 0.05330 0.04737 -0.0048 0.0139 1.0000
14.250 1.2330 0.05724 0.05142 -0.0058 0.0135 1.0000
14.500 1.2256 0.06152 0.05586 -0.0072 0.0129 1.0000
14.750 1.2188 0.06593 0.06045 -0.0087 0.0124 1.0000
15.000 1.2103 0.07079 0.06549 -0.0107 0.0120 1.0000
15.250 1.2011 0.07601 0.07088 -0.0131 0.0116 1.0000
15.500 1.1902 0.08174 0.07676 -0.0159 0.0114 1.0000
15.750 1.1783 0.08787 0.08305 -0.0190 0.0112 1.0000
16.000 1.1664 0.09428 0.08961 -0.0225 0.0109 1.0000
16.250 1.1529 0.10114 0.09662 -0.0262 0.0108 1.0000
16.500 1.1389 0.10839 0.10403 -0.0303 0.0107 1.0000
16.750 1.1249 0.11581 0.11159 -0.0344 0.0107 1.0000
17.000 1.1100 0.12364 0.11956 -0.0389 0.0106 1.0000
17.250 1.0951 0.13174 0.12780 -0.0436 0.0105 1.0000
17.500 1.0803 0.14006 0.13624 -0.0485 0.0104 1.0000
17.750 1.0642 0.14893 0.14525 -0.0538 0.0104 1.0000
18.000 1.0439 0.15935 0.15583 -0.0599 0.0106 1.0000
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Polar data table (+)
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