RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 30 AIRFOIL (raf30-il) Reynolds number: 200,000 Max Cl/Cd: 52.28 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf30-il-200000.txt Download as CSV file: xf-raf30-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7279 0.10867 0.10473 -0.0199 1.0000 0.0491
-13.750 -0.7197 0.10703 0.10310 -0.0197 1.0000 0.0497
-13.500 -0.9410 0.06599 0.06111 -0.0481 1.0000 0.0407
-13.250 -0.9636 0.06193 0.05684 -0.0487 1.0000 0.0405
-13.000 -0.9843 0.05776 0.05248 -0.0482 1.0000 0.0407
-12.750 -1.0018 0.05457 0.04908 -0.0467 1.0000 0.0407
-12.500 -1.0170 0.05133 0.04562 -0.0445 1.0000 0.0408
-12.250 -1.0273 0.04853 0.04263 -0.0417 1.0000 0.0410
-12.000 -1.0323 0.04587 0.03983 -0.0390 1.0000 0.0415
-11.750 -1.0362 0.04357 0.03735 -0.0358 1.0000 0.0417
-11.500 -1.0335 0.04144 0.03505 -0.0334 1.0000 0.0423
-11.250 -1.0262 0.03949 0.03297 -0.0313 1.0000 0.0430
-11.000 -1.0185 0.03776 0.03108 -0.0291 1.0000 0.0440
-10.750 -1.0105 0.03607 0.02918 -0.0268 1.0000 0.0451
-10.500 -1.0013 0.03443 0.02730 -0.0244 1.0000 0.0462
-10.250 -0.9900 0.03283 0.02544 -0.0222 1.0000 0.0471
-10.000 -0.9770 0.03143 0.02378 -0.0201 1.0000 0.0478
-9.750 -0.9581 0.02898 0.02121 -0.0192 1.0000 0.0492
-9.500 -0.9393 0.02764 0.01989 -0.0181 1.0000 0.0510
-9.250 -0.9215 0.02653 0.01872 -0.0167 1.0000 0.0526
-9.000 -0.9030 0.02542 0.01751 -0.0152 1.0000 0.0541
-8.750 -0.8845 0.02441 0.01640 -0.0137 1.0000 0.0557
-8.500 -0.8664 0.02364 0.01550 -0.0121 1.0000 0.0571
-8.250 -0.8495 0.02213 0.01407 -0.0105 1.0000 0.0594
-8.000 -0.8334 0.02127 0.01322 -0.0086 1.0000 0.0615
-7.750 -0.8174 0.02049 0.01242 -0.0066 1.0000 0.0637
-7.500 -0.8013 0.01982 0.01169 -0.0045 1.0000 0.0663
-7.250 -0.7883 0.01892 0.01082 -0.0020 1.0000 0.0694
-7.000 -0.7745 0.01823 0.01015 0.0004 1.0000 0.0732
-6.750 -0.7597 0.01764 0.00952 0.0028 1.0000 0.0778
-6.500 -0.7482 0.01687 0.00884 0.0056 1.0000 0.0846
-6.250 -0.7363 0.01617 0.00823 0.0083 1.0000 0.0974
-6.000 -0.7277 0.01526 0.00754 0.0116 1.0000 0.1306
-5.750 -0.7192 0.01444 0.00700 0.0147 1.0000 0.1770
-5.500 -0.7089 0.01384 0.00667 0.0175 1.0000 0.2238
-5.250 -0.6969 0.01343 0.00645 0.0201 1.0000 0.2688
-5.000 -0.6846 0.01309 0.00628 0.0225 1.0000 0.3082
-4.500 -0.6282 0.01246 0.00601 0.0211 0.9925 0.3999
-4.250 -0.5903 0.01217 0.00592 0.0187 0.9854 0.4514
-4.000 -0.5530 0.01195 0.00585 0.0166 0.9778 0.4972
-3.750 -0.5134 0.01180 0.00580 0.0141 0.9712 0.5385
-3.500 -0.4786 0.01165 0.00575 0.0127 0.9623 0.5739
-3.250 -0.4375 0.01154 0.00570 0.0101 0.9568 0.6050
-3.000 -0.4031 0.01141 0.00561 0.0089 0.9477 0.6285
-2.750 -0.3608 0.01128 0.00549 0.0062 0.9426 0.6507
-2.500 -0.3246 0.01117 0.00544 0.0047 0.9345 0.6718
-2.250 -0.2851 0.01108 0.00537 0.0028 0.9282 0.6973
-2.000 -0.2491 0.01098 0.00533 0.0016 0.9198 0.7164
-1.750 -0.2110 0.01085 0.00521 -0.0001 0.9119 0.7321
-1.500 -0.1784 0.01075 0.00511 -0.0007 0.9009 0.7467
-1.250 -0.1428 0.01064 0.00501 -0.0018 0.8907 0.7600
-1.000 -0.1106 0.01054 0.00492 -0.0021 0.8779 0.7728
-0.750 -0.0825 0.01049 0.00486 -0.0016 0.8636 0.7856
-0.500 -0.0553 0.01046 0.00483 -0.0010 0.8500 0.7988
-0.250 -0.0285 0.01044 0.00480 -0.0004 0.8370 0.8124
0.000 0.0000 0.01044 0.00480 0.0000 0.8248 0.8248
0.250 0.0285 0.01044 0.00480 0.0004 0.8124 0.8370
0.500 0.0553 0.01046 0.00483 0.0010 0.7988 0.8500
0.750 0.0825 0.01049 0.00486 0.0016 0.7856 0.8636
1.000 0.1106 0.01054 0.00492 0.0021 0.7728 0.8779
1.250 0.1428 0.01064 0.00501 0.0018 0.7601 0.8907
1.500 0.1784 0.01075 0.00512 0.0007 0.7467 0.9009
1.750 0.2111 0.01085 0.00521 0.0001 0.7320 0.9119
2.000 0.2491 0.01098 0.00534 -0.0016 0.7166 0.9198
2.250 0.2850 0.01107 0.00537 -0.0028 0.6971 0.9282
2.500 0.3245 0.01116 0.00543 -0.0047 0.6718 0.9345
2.750 0.3609 0.01128 0.00549 -0.0062 0.6509 0.9426
3.000 0.4031 0.01142 0.00561 -0.0089 0.6285 0.9477
3.250 0.4376 0.01154 0.00570 -0.0101 0.6049 0.9568
3.500 0.4787 0.01165 0.00574 -0.0127 0.5734 0.9624
3.750 0.5133 0.01180 0.00580 -0.0141 0.5385 0.9711
4.000 0.5531 0.01195 0.00585 -0.0166 0.4973 0.9778
4.250 0.5904 0.01217 0.00592 -0.0187 0.4514 0.9854
4.500 0.6283 0.01246 0.00601 -0.0212 0.3996 0.9926
4.750 0.6675 0.01280 0.00612 -0.0240 0.3472 0.9991
5.000 0.6844 0.01309 0.00627 -0.0225 0.3071 1.0000
5.250 0.6968 0.01343 0.00645 -0.0200 0.2683 1.0000
5.500 0.7088 0.01384 0.00667 -0.0175 0.2238 1.0000
5.750 0.7190 0.01444 0.00701 -0.0147 0.1764 1.0000
6.000 0.7276 0.01526 0.00755 -0.0116 0.1302 1.0000
6.250 0.7362 0.01617 0.00823 -0.0083 0.0974 1.0000
6.500 0.7481 0.01687 0.00884 -0.0055 0.0845 1.0000
6.750 0.7596 0.01764 0.00952 -0.0027 0.0778 1.0000
7.000 0.7744 0.01823 0.01015 -0.0004 0.0732 1.0000
7.250 0.7882 0.01893 0.01083 0.0020 0.0694 1.0000
7.500 0.8012 0.01983 0.01170 0.0045 0.0664 1.0000
7.750 0.8175 0.02049 0.01242 0.0066 0.0638 1.0000
8.000 0.8334 0.02127 0.01322 0.0086 0.0615 1.0000
8.250 0.8495 0.02212 0.01406 0.0105 0.0595 1.0000
8.500 0.8665 0.02365 0.01551 0.0120 0.0571 1.0000
8.750 0.8846 0.02443 0.01641 0.0137 0.0557 1.0000
9.000 0.9031 0.02544 0.01753 0.0152 0.0541 1.0000
9.250 0.9215 0.02652 0.01870 0.0167 0.0525 1.0000
9.500 0.9393 0.02762 0.01987 0.0181 0.0509 1.0000
9.750 0.9582 0.02899 0.02122 0.0192 0.0493 1.0000
10.000 0.9772 0.03145 0.02380 0.0200 0.0479 1.0000
10.250 0.9903 0.03283 0.02543 0.0221 0.0471 1.0000
10.500 1.0014 0.03443 0.02730 0.0244 0.0462 1.0000
10.750 1.0105 0.03611 0.02923 0.0268 0.0451 1.0000
11.000 1.0186 0.03778 0.03110 0.0291 0.0440 1.0000
11.250 1.0267 0.03947 0.03294 0.0312 0.0430 1.0000
11.500 1.0332 0.04147 0.03509 0.0334 0.0423 1.0000
11.750 1.0357 0.04364 0.03743 0.0359 0.0418 1.0000
12.000 1.0315 0.04592 0.03989 0.0391 0.0416 1.0000
12.250 1.0274 0.04837 0.04249 0.0418 0.0411 1.0000
12.500 1.0161 0.05122 0.04554 0.0446 0.0409 1.0000
12.750 1.0025 0.05453 0.04904 0.0466 0.0407 1.0000
13.000 0.9847 0.05829 0.05299 0.0480 0.0405 1.0000
13.250 0.9627 0.06245 0.05737 0.0485 0.0404 1.0000
13.500 0.9392 0.06604 0.06119 0.0479 0.0408 1.0000
13.750 0.6283 0.09894 0.09524 0.0262 0.0498 1.0000
14.000 0.6277 0.10251 0.09881 0.0251 0.0491 1.0000
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